Airworthiness Directives; Boeing Model 727, 727C, 727-100, -100C, and -200 Series Airplanes

[Federal Register Volume 69, Number 173 (Wednesday, September 8, 2004)]
[Rules and Regulations]
[Pages 54211-54213]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-20205]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-131-AD; Amendment 39-13786; AD 2004-18-08]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727, 727C, 727-100, -100C, 
and -200 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Boeing Model 727, 727C, 727-100, -100C, and -200 
series airplanes. This amendment requires an inspection of the forward 
trunnion attach fittings of the main landing gear (MLG), inspections of 
the attach fitting holes of the forward trunnion attach fittings if 
necessary, replacement of the forward trunnion attach fittings if 
necessary, and corrective actions if necessary. This action is 
necessary to detect and correct cracks and corrosion on the attach 
fitting holes of the forward trunnion attach fittings of the MLG, which 
could result in the collapse of the MLG. This action is intended to 
address the identified unsafe condition.

DATES: Effective October 13, 2004.
    The incorporation by reference of a certain publication listed in 
the regulations is approved by the Director of the Federal Register as 
of October 13, 2004.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplanes, 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 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/code_of_federal_regulations/ibr_locations.html.

FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6456; fax (425) 917-6590.

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 727, 727C, 
727-100, -100C, and -200 series airplanes was published in the Federal 
Register on June 16, 2004 (69 FR 33587). That action proposed to 
require an inspection of the forward trunnion attach fittings of the 
main landing gear, inspections of the attach fitting holes of the 
forward trunnion attach fittings if necessary, replacement of the 
forward trunnion attach fittings if necessary, and corrective actions 
if necessary.

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 523 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 309 airplanes of U.S. registry 
will be affected by this AD, that it will take approximately 1 work 
hour per airplane to accomplish the required inspection, and that the 
average labor rate is $65 per work hour. Based on these figures, the

[[Page 54212]]

cost impact of the AD on U.S. operators is estimated to be $20,085, or 
$65 per airplane.
    The cost impact figure discussed above is 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. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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

0
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

0
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]

0
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2004-18-08 Boeing: Amendment 39-13786. Docket 2003-NM-131-AD.

    Applicability: Model 727, 727C, 727-100, -100C, and -200 series 
airplanes, line numbers 1 through 887 inclusive; certificated in any 
category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct cracks and corrosion on the attach fitting 
holes of the forward trunnion attach fittings of the main landing 
gear (MLG), which could result in the collapse of the MLG, 
accomplish the following:

Service Bulletin References

    (a) The term ``service bulletin,'' as used in this AD, means 
Boeing Alert Service Bulletin 727-57A0132, Revision 3, dated March 
20, 2003.

Initial Inspection

    (b) Perform an inspection of the forward trunnion attach 
fittings of the MLG to determine the part number (P/N) of the attach 
fitting, in accordance with ``Part 1'' of the Accomplishment 
Instructions of the service bulletin, at the latest of the times 
specified in paragraphs (b)(1), (b)(2), and (b)(3) of this AD:
    (1) Prior to airplanes reaching 240 months old since the date of 
issuance of the original Airworthiness Certificate or the date of 
issuance of the original Export Certificate of Airworthiness; or
    (2) Within 18 months after the effective date of this AD; or
    (3) Within 120 months after the last inspection/rework/repair of 
the attach fitting per Boeing Service Bulletin 727-57A0132, dated 
June 28, 1974, Revision 1, dated October 31, 1975, or Revision 2, 
dated April 24, 1981; or Boeing Alert Service Bulletin 727-57A0132, 
Revision 3, dated March 20, 2003.

Corrective Actions

    (c) If, during the inspection required by paragraph (b) of this 
AD, both attach fittings are found to have P/N 65-19296-9, -10, -13, 
or -14; P/N 65-99909-1724 or -1727; P/N 65-19296U13 or P/N 65-
19296U14 (attach fitting made of 7075-T73511 or 7050-T7451 
aluminum); no further action is required by this paragraph.
    (d) If, during the inspection required by paragraph (b) of this 
AD, any attach fitting is found to have P/N 65-19296-1 through -8 
inclusive (attach fitting made of 7079-T6 aluminum): Before further 
flight, perform the actions in paragraphs (d)(1) and (d)(2) of this 
AD, as applicable.
    (1) Do detailed and high frequency eddy current inspections of 
the attach fitting holes for cracks and corrosion, repair any crack 
or corrosion found, and rework the attach fitting holes, in 
accordance with Figures 4 and 5 of the service bulletin, except as 
provided by paragraph (d)(2) of this AD.
    (2) If the attach fitting hole cannot be reworked or repaired in 
accordance with Figures 4 and 5 of the service bulletin: Before 
further flight, replace the attach fitting with a new attach fitting 
that has P/N 65-19296-9, -10, -13, or -14, P/N 65-99909-1724 or -
1727, P/N 65-19296U13, or P/N 65-19296U14, in accordance with 
paragraph 7 of ``Part II'' of the Accomplishment Instructions of the 
service bulletin. Accomplishment of this replacement is terminating 
action for that fitting.

Terminating Action

    (e) Within 120 months after the effective date of this AD, 
replace attach fittings that have P/N 65-19296-1 through -8 (attach 
fittings made of 7079-T6 aluminum) with new attach fittings that 
have P/N 65-19296-9, -10, -13, or -14, P/N 65-99909-1724 or -1727, 
P/N 65-19296U13, or P/N 65-19296U14 (attach fittings made of 7075-
T73511 or 7050-T7451 aluminum), in accordance with paragraph 7 of 
``Part II'' of the Accomplishment Instructions of the service 
bulletin. Replacement of all attach fittings made of 7079-T6 
aluminum with new attach fittings made of 7075-T73511 or 7050-T7451 
aluminum terminates the requirements of paragraph (d) of this AD.

Parts Installation

    (f) As of the effective date of this AD, no person shall 
install, on any airplane, an attach fitting, P/N 65-19296-1, -2, -3, 
-4, -5, -6, -7, or -8 (attach fitting made of 7079-T6 aluminum), 
unless it has been inspected/reworked/repaired in accordance with 
paragraph (d) of this AD.

Alternative Methods of Compliance

    (g)(1) In accordance with 14 CFR 39.19, the Manager, Seattle 
Aircraft Certification Office, FAA, is authorized to approve 
alternative methods of compliance (AMOCs) for this AD.
    (2) An AMOC that provides an acceptable level of safety may be 
used for any rework/repair required by this AD, if it is approved by 
a Boeing Company Designated Engineering Representative (DER) who has 
been authorized by the Manager, Seattle ACO, to make such findings. 
For a rework/repair method to be approved, the approval must 
specifically reference this AD.

Incorporation by Reference

    (h) The actions shall be done in accordance with Boeing Alert 
Service Bulletin 727-57A0132, Revision 3, dated March 20, 2003. This 
incorporation by reference was approved by 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 Airplanes, 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 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/code_of_federal_regulations/ibr_locations.html.

Effective Date

    (i) This amendment becomes effective on October 13, 2004.


[[Page 54213]]


    Issued in Renton, Washington, on August 26, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-20205 Filed 9-7-04; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T04:02:13.491980+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

194fd712955f2da5788940eaa9a54a877be6ae8e6208944e4b02eee67e60da2a

Text SHA-256

dc352e2652e7fbca923a6fb72d9efb0c86976b9ec302ec7941b50dfee13cd1e6