[Federal Register Volume 64, Number 243 (Monday, December 20, 1999)]
[Rules and Regulations]
[Pages 71007-71009]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-32191]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-114-AD; Amendment 39-11462; AD 99-26-02]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-400 and 767 Series 
Airplanes Powered by Pratt & Whitney PW4000 Series Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Boeing Model 747-400 and 767 series airplanes, 
that requires replacement of the existing deactivation pin, pin 
bushing, and insert flange on each thrust reverser half, with new, 
improved components. This amendment is prompted by reports of partial 
deployment of deactivated thrust reversers during landing. The actions 
specified by this AD are intended to prevent failure of the thrust 
reverser deactivation pins, which could result in deployment of the 
thrust reverser in flight and consequent reduced controllability of the 
airplane.

DATES: Effective January 24, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 24, 2000.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of 
the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: Dorr Anderson, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Transport Airplane Directorate, 
Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
Washington

[[Page 71008]]

98055-4056; telephone (425) 227-2684; fax (425) 227-1181.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Boeing Model 747-400 and 
767 series airplanes was published in the Federal Register on September 
15, 1999 (64 FR 50022). That action proposed to require replacement of 
the existing deactivation pin, pin bushing, and insert flange on each 
thrust reverser half, with new, improved components.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.
    The commenter supports the proposed rule.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Cost Impact

    There are approximately 201 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 39 Model 747-400 series 
airplanes and 54 Model 767 series airplanes of U.S. registry will be 
affected by this AD. It will take approximately 6 work hours per engine 
accomplish the required replacement, at an average labor rate of $60 
per work hour. Required parts will cost approximately $3,956 per 
engine. Based on these figures, the cost impact of this AD on U.S. 
operators of Model 747-400 series airplanes (4 engines per airplane) is 
estimated to be $673,296, or $17,264 per airplane. The cost impact of 
this AD on U.S. operators of Model 767 series airplanes (2 engines per 
airplane) is estimated to be $466,128, or $8,632 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the requirements of this 
AD action, and that no operator would accomplish those actions in the 
future if this AD were not adopted.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

99-26-02  Boeing: Amendment 39-11462. Docket 99-NM-114-AD.

    Applicability: Model 747-400 series airplanes powered by Pratt & 
Whitney PW4000 series engines, as listed in Boeing Service Bulletin 
747-78A2165, Revision 1, dated May 13, 1999; and Model 767 series 
airplanes powered by Pratt & Whitney PW4000 series engines, as 
listed in Boeing Alert Service Bulletin 767-78A0080, dated February 
25, 1999; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (b) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent failure of the thrust reverser deactivation pins, 
which could result in deployment of the thrust reverser in flight 
and consequent reduced controllability of the airplane, accomplish 
the following:

Replacement

    (a) Within 24 months after the effective date of this AD, 
replace the existing deactivation pin, pin bushing in the aft 
cascade mounting ring, and insert flange on each thrust reverser 
half, with new, improved components, in accordance with Boeing 
Service Bulletin 747-78A2165, Revision 1, dated May 13, 1999 (for 
Model 747-400 series airplanes); or Boeing Alert Service Bulletin 
767-78A0080, dated February 25, 1999 (for Model 767 series 
airplanes); as applicable.

    Note 2: The new, improved insert flange and pin bushing does not 
preclude use of a deactivation pin having P/N 315T1604-2 or -5. 
However, use of deactivation pins having P/N 315T1604-2 or -5 may 
not prevent the thrust reversers from deploying in event of a full 
powered deployment. Therefore, thrust reversers modified per this AD 
require installation of the new, longer deactivation pins having P/N 
315T1604-6, as specified in the applicable service bulletin.

    Note 3: Replacements accomplished prior to the effective date of 
this AD in accordance with Boeing Alert Service Bulletin 747-
78A2165, dated February 25, 1999, are considered acceptable for 
compliance with the applicable action specified in this amendment.

Alternative Methods of Compliance

    (b) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Seattle Aircraft Certification 
Office (ACO), FAA, Transport Airplane Directorate. Operators shall 
submit their requests through an appropriate FAA Principal 
Maintenance Inspector, who may add comments and then send it to the 
Manager, Seattle ACO.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permits

    (c) Special flight permits may be issued in accordance 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the airplane to a location where the 
requirements of this AD can be accomplished.

Incorporation by Reference

    (d) The actions shall be done in accordance with Boeing Service 
Bulletin 747-78A2165, Revision 1, dated May 13, 1999, or Boeing 
Alert Service Bulletin 767-78A0080, dated February 25, 1999, as 
applicable. This incorporation by reference was approved by

[[Page 71009]]

the Director of the Federal Register in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. Copies may be obtained from Boeing 
Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-
2207. Copies may be inspected at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.
    (e) This amendment becomes effective on January 24, 2000.

    Issued in Renton, Washington, on December 7, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-32191 Filed 12-17-99; 8:45 am]
BILLING CODE 4910-13-P