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Airworthiness Directives; Fokker Model F27 Mark 050, 200, 300, 400, 500, 600, and 700 Airplanes

Document Details

Information about this document as published in the Federal Register.

Published Document

This document has been published in the Federal Register. Use the PDF linked in the document sidebar for the official electronic format.

Start Preamble

AGENCY:

Federal Aviation Administration (FAA), Department of Transportation (DOT).

ACTION:

Final rule.

SUMMARY:

We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, * * * Special Federal Aviation Regulation 88 (SFAR88) * * * required a Start Printed Page 13072safety review of the aircraft Fuel Tank System * * *.

* * * * *

Fuel Airworthiness Limitations are items arising from a systems safety analysis that have been shown to have failure mode(s) associated with an ‘unsafe condition' * * *. These are identified in Failure Conditions for which an unacceptable probability of ignition risk could exist if specific tasks and/or practices are not performed in accordance with the manufacturers' requirements.

We are issuing this AD to require actions to correct the unsafe condition on these products.

DATES:

This AD becomes effective April 16, 2008.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of April 16, 2008.

ADDRESSES:

You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

Start Further Info

FOR FURTHER INFORMATION CONTACT:

Tom Rodriguez, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1137; fax (425) 227-1149.

End Further Info End Preamble Start Supplemental Information

SUPPLEMENTARY INFORMATION:

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on September 11, 2007 (72 FR 51719). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:

Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, the FAA published Special Federal Aviation Regulation 88 (SFAR 88) in June 2001. SFAR 88 required a safety review of the aircraft Fuel Tank System to determine that the design meets the requirements of FAR (Federal Aviation Regulation) § 25.901 and § 25.981(a) and (b).

A similar regulation has been recommended by the JAA (Joint Aviation Authorities) to the European National Aviation Authorities in JAA letter 04/00/02/07/03-L024 of 3 February 2003. The review was requested to be mandated by NAA's (National Aviation Authorities) using JAR (Joint Aviation Regulation) § 25.901(c), § 25.1309.

In August 2005 EASA published a policy statement on the process for developing instructions for maintenance and inspection of Fuel Tank System ignition source prevention (EASA D 2005/CPRO, http://www.easa.eu.int/​home/​cert_​policy_​statements_​en.html) that also included the EASA expectations with regard to compliance times of the corrective actions on the unsafe and the not unsafe part of the harmonised design review results. On a global scale the TC (type certificate) holders committed themselves to the EASA published compliance dates (see EASA policy statement). The EASA policy statement has been revised in March 2006: the date of 31-12-2005 for the unsafe related actions has now been set at 01-07-2006.

Fuel Airworthiness Limitations are items arising from a systems safety analysis that have been shown to have failure mode(s) associated with an ‘unsafe condition' as defined in FAA's memo 2003-112-15 ‘SFAR 88—Mandatory Action Decision Criteria'. These are identified in Failure Conditions for which an unacceptable probability of ignition risk could exist if specific tasks and/or practices are not performed in accordance with the manufacturers' requirements.

This EASA Airworthiness Directive mandates the Fuel System Airworthiness Limitations, comprising maintenance/inspection tasks and Critical Design Configuration Control Limitations (CDCCL) for the type of aircraft, that resulted from the design reviews and the JAA recommendation and EASA policy statement mentioned above.

The corrective action includes revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. You may obtain further information by examining the MCAI in the AD docket.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public.

Actions Since the NPRM Was Issued

Since we issued the NPRM, we have received Fokker 50/60 Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL) Report SE-671, Issue 2, dated December 1, 2006. (We referred to Fokker 50/60 Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL) Report SE-671, Issue 1, dated January 31, 2006, in the NPRM as the appropriate source of service information for accomplishing the required actions.) Issue 2 of the report includes the CDCCL control references as published in the May 1, 2006, revision of the airplane maintenance manual. We have changed paragraphs (f) and (h) of the AD to refer to Issue 2 of the report.

We have also received Fokker Service Bulletin SBF27-28-070, Revision 1, dated January 8, 2008. (We referred to Fokker Service Bulletin SBF27/28-070, dated June 30, 2006, in the NPRM as an appropriate source of service information for accomplishing the required actions.) Revision 1 of the service bulletin includes editorial changes, changes to certain CDCCL control references, and changes to the compliance paragraph. We have changed paragraphs (f) and (h) of the AD to refer to Revision 1 of the service bulletin.

We have also added a new paragraph (f)(5) to the AD to specify that actions done before the effective date of this AD in accordance with Fokker 50/60 Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL) Report SE-671, Issue 1, dated January 31, 2006; or Fokker Service Bulletin SBF27/28-070, dated June 30, 2006; as applicable; are acceptable for compliance with the corresponding requirements of this AD.

Explanation of Additional Changes to the AD

We have clarified paragraph (f)(1) of this AD to specify that operators are to incorporate the “limits” (inspections, thresholds, and intervals) specified in the Fokker 50/60 Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL) Report SE-671, Issue 2, dated December 1, 2006; or Fokker Service Bulletin SBF27-28-070, Revision 1, dated January 8, 2008; as applicable. Paragraph (f)(1) of the NPRM did not include the words “the limits,” or a description of those limits.

For standardization purposes, we have revised this AD in the following ways:

  • We have revised paragraph (f)(4) of this AD to specify that no alternative inspections, inspection intervals, or CDCCLs may be used unless they are part of a later approved revision of Fokker 50/60 Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL) Report SE-671, Issue 2, dated December 1, 2006; or Fokker Service Bulletin SBF27-28-070, Revision 1, dated January 8, 2008; as applicable; or unless they are approved as an alternative method of compliance (AMOC). Inclusion of this paragraph in the AD is intended to ensure that the AD-mandated airworthiness limitations changes are treated the same as the airworthiness limitations issued with the original type certificate.
  • We have simplified the language in Note 1 of this AD to clarify that an operator must request approval for an AMOC if the operator cannot Start Printed Page 13073accomplish the required inspections because an airplane has been previously modified, altered, or repaired in the areas addressed by the required inspections.
  • In most ADs, we adopt a compliance time allowing a specified amount of time after the AD's effective date. In this case, however, the FAA has already issued regulations that require operators to revise their maintenance/inspection programs to address fuel tank safety issues. The compliance date for these regulations is December 16, 2008. To provide for coordinated implementation of these regulations and this AD, we are including this same compliance date in this AD.

Conclusion

We reviewed the available data and determined that air safety and the public interest require adopting the AD with the changes described previously. We determined that these changes will not increase the economic burden on any operator or increase the scope of the AD.

Differences Between This AD and the MCAI or Service Information

We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information.

We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD.

Costs of Compliance

We estimate that this AD will affect about 24 products of U.S. registry. We also estimate that it will take about 1 work-hour per product to comply with the basic requirements of this AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $1,920, or $80 per product.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. “Subtitle VII: Aviation Programs,” describes in more detail the scope of the Agency's authority.

We are issuing this rulemaking under the authority described in “Subtitle VII, Part A, Subpart III, Section 44701: General requirements.” Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.

Regulatory Findings

We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify this AD:

1. Is not a “significant regulatory action” under Executive Order 12866;

2. Is not a “significant rule” under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and

3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket.

Examining the AD Docket

You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.

Start List of Subjects

List of Subjects in 14 CFR Part 39

End List of Subjects

Adoption of the Amendment

Start Amendment Part

Accordingly, under the authority delegated to me by the Administrator, the FAA amends

End Amendment Part Start Part

PART 39—AIRWORTHINESS DIRECTIVES

End Part Start Amendment Part

1. The authority citation for part 39 continues to read as follows:

End Amendment Part Start Authority

Authority: 49 U.S.C. 106(g), 40113, 44701.

End Authority
[Amended]
Start Amendment Part

2. The FAA amends § 39.13 by adding the following new AD:

End Amendment Part

2008-05-18 Fokker Services B.V.: Amendment 39-15412. Docket No. FAA-2007-29172; Directorate Identifier 2006-NM-285-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective April 16, 2008.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Fokker Model F27 Mark 050 airplanes, all serial numbers; and Fokker F27 Mark 200, 300, 400, 500, 600, and 700 airplanes, serial numbers 10102 through 10692; certificated in any category.

Note 1:

This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (g)(1) of this AD. The request should include a description of changes to the required inspections that will ensure the continued operational safety of the airplane.

Subject

(d) Air Transport Association (ATA) of America Code 28: Fuel.

Reason

(e) The mandatory continuing airworthiness information (MCAI) states:

Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, the FAA published Special Federal Aviation Regulation 88 (SFAR 88) in June 2001. SFAR 88 required a safety review of the aircraft Fuel Tank System to determine that the design meets the requirements of FAR (Federal Aviation Regulation) § 25.901 and § 25.981(a) and (b).

A similar regulation has been recommended by the JAA (Joint Aviation Authorities) to the European National Aviation Authorities in JAA letter 04/00/02/07/03-L024 of 3 February 2003. The review was requested to be mandated by NAA's (National Aviation Authorities) using JAR (Joint Aviation Regulation) § 25.901(c), § 25.1309.

In August 2005 EASA published a policy statement on the process for developing instructions for maintenance and inspection of Fuel Tank System ignition source prevention (EASA D 2005/CPRO, http://Start Printed Page 13074www.easa.eu.int/​home/​cert_​policy_​statements_​en.html) that also included the EASA expectations with regard to compliance times of the corrective actions on the unsafe and the not unsafe part of the harmonised design review results. On a global scale the TC (type certificate) holders committed themselves to the EASA published compliance dates (see EASA policy statement). The EASA policy statement has been revised in March 2006: the date of 31-12-2005 for the unsafe related actions has now been set at 01-07-2006.

Fuel Airworthiness Limitations are items arising from a systems safety analysis that have been shown to have failure mode(s) associated with an ‘unsafe condition' as defined in FAA's memo 2003-112-15 ‘SFAR 88—Mandatory Action Decision Criteria'. These are identified in Failure Conditions for which an unacceptable probability of ignition risk could exist if specific tasks and/or practices are not performed in accordance with the manufacturers' requirements.

This EASA Airworthiness Directive mandates the Fuel System Airworthiness Limitations, comprising maintenance/inspection tasks and Critical Design Configuration Control Limitations (CDCCL) for the type of aircraft, that resulted from the design reviews and the JAA recommendation and EASA policy statement mentioned above.

The corrective action includes revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems.

Actions and Compliance

(f) Unless already done, do the following actions.

(1) Within 3 months after the effective date of this AD or before December 16, 2008, whichever occurs first, revise the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate the limits (inspections, thresholds, and intervals) specified in Fokker 50/60 Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL) Report SE-671, Issue 2, dated December 1, 2006; or Fokker Service Bulletin SBF27-28-070, Revision 1, dated January 8, 2008; as applicable. For all tasks identified in Report SE-671 or Service Bulletin SBF27-28-070, the initial compliance times are as specified in Table 1 or Table 2 of this AD, as applicable. The repetitive inspections must be accomplished thereafter at the intervals specified in Report SE-671 or Service Bulletin SBF27-28-070, as applicable, except as provided by paragraphs (f)(3) and (g)(1) of this AD.

Table 1.—Initial Compliance Times for ALS Revision for Model F27 Mark 050 Airplanes

For—The later of—
Task 280000-01102 months after the effective date of this AD; or 102 months after the date of issuance of the original Dutch standard airworthiness certificate or the date of issuance of the original Dutch export certificate of airworthiness.
Task 280000-0230 months after the effective date of this AD; or 30 months after the date of issuance of the original Dutch standard airworthiness certificate or the date of issuance of the original Dutch export certificate of airworthiness.

Table 2.—Initial Compliance Times for ALS Revision for Model F27 Mark 200, 300, 400, 500, 600, and 700 Airplanes

For—The later of—
Task 280000-0178 months after the effective date of this AD; or 78 months after the date of issuance of the original Dutch standard airworthiness certificate or the date of issuance of the original Dutch export certificate of airworthiness.
Task 280000-0218 months after the effective date of this AD; or 18 months after the date of issuance of the original Dutch standard airworthiness certificate or the date of issuance of the original Dutch export certificate of airworthiness.

(2) Within 3 months after the effective date of this AD or before December 16, 2008, whichever occurs first, revise the ALS of the Instructions for Continued Airworthiness to incorporate the CDCCLs as defined in Fokker 50/60 Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL) Report SE-671, Issue 2, dated December 1, 2006; or Fokker Service Bulletin SBF27-28-070, Revision 1, dated January 8, 2008; as applicable.

(3) Where Fokker 50/60 Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL) Report SE-671, Issue 2, dated December 1, 2006; or Fokker Service Bulletin SBF27-28-070, Revision 1, dated January 8, 2008; as applicable; allow for exceptional short-term extensions, an exception is acceptable to the FAA if it is approved by the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office.

(4) After accomplishing the actions specified in paragraphs (f)(1) and (f)(2) of this AD, no alternative inspections, inspection intervals, or CDCCLs may be used, unless the inspections, inspection intervals, or CDCCLs are part of a later revision of Fokker 50/60 Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL) Report SE-671, Issue 2, dated December 1, 2006; or Fokker Service Bulletin SBF27-28-070, Revision 1, dated January 8, 2008; as applicable; that is approved by the Manager, International Branch, ANM-116, FAA, or the Civil Aviation Authority—The Netherlands (CAA-NL) (or its delegated agent); or unless the inspections, intervals, or CDCCLs are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (g)(1) of this AD.

(5) Actions done before the effective date of this AD in accordance with Fokker 50/60 Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL) Report SE-671, Issue 1, dated January 31, 2006; and Fokker Service Bulletin SBF27-28-070, dated June 30, 2006; are acceptable for compliance with the corresponding requirements of this AD.

FAA AD Differences

Note 2:

This AD differs from the MCAI and/or service information as follows: No differences.

Other FAA AD Provisions

(g) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Tom Rodriguez, Aerospace Engineer, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1137; fax (425) 227-1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they Start Printed Page 13075are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

(3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120-0056.

Related Information

(h) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2006-0207, dated July 12, 2006; EASA Airworthiness Directive 2006-0209, dated July 12, 2006 (corrected September 1, 2006); Fokker 50/60 Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL) Report SE-671, Issue 2, dated December 1, 2006; and Fokker Service Bulletin SBF27-28-070, Revision 1, dated January 8, 2008; for related information.

Material Incorporated by Reference

(i) You must use Fokker 50/60 Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL) Report SE-671, Issue 2, dated December 1, 2006; and Fokker Service Bulletin SBF27-28-070, Revision 1, dated January 8, 2008; to do the actions required by this AD, unless the AD specifies otherwise.

(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) For service information identified in this AD, contact Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands.

(3) You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/​federal-register/​cfr/​ibr-locations.html.

Start Signature

Issued in Renton, Washington, on February 28, 2008.

Ali Bahrami,

Manager, Transport Airplane Directorate, Aircraft Certification Service.

End Signature End Supplemental Information

[FR Doc. E8-4328 Filed 3-11-08; 8:45 am]

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