Airworthiness Directives; Boeing Model 707 and 720 Series Airplanes

[Federal Register Volume 69, Number 66 (Tuesday, April 6, 2004)]
[Rules and Regulations]
[Pages 17925-17926]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-7126]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-335-AD; Amendment 39-13550; AD 2004-07-06]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 707 and 720 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Boeing Model 707 and 720 series airplanes, that 
requires repetitive inspections of the upper and lower barrel nuts and 
bolts that retain the aft trunnion support fitting of each main landing 
gear for corrosion, cracks, and loose or missing nuts and bolts; torque 
checks of the upper and lower bolts to verify the torque is within a 
specified range; and corrective actions, if necessary. This action is 
necessary to detect and correct cracking and/or loss of the barrel nuts 
and bolts that retain the aft trunnion support fitting, which could 
result in the collapse of the main landing gear upon landing. This 
action is intended to address the identified unsafe condition.

DATES: Effective May 11, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 11, 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 Office of 
the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: Candice Gerretsen, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6428; 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 707 and 720 
series airplanes was published in the Federal Register on December 18, 
2003 (68 FR 70477). That action proposed to require repetitive 
inspections of the upper and lower barrel nuts and bolts that retain 
the aft trunnion support fitting of each main landing gear for 
corrosion, cracks, and loose or missing nuts and bolts; torque checks 
of the upper and lower bolts to verify the torque is within a specified 
range; and corrective actions, if necessary.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. We received no comments on the 
proposal or on the determination of the cost to the public.

Conclusion

    After careful review of the available data, we have determined that 
air safety and the public interest require the adoption of the rule as 
proposed.

Cost Impact

    There are approximately 230 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 42 airplanes of U.S. registry 
will be affected by this AD.
    It will take approximately 1 work hour per airplane to accomplish 
the required detailed inspection of the upper and lower barrel nuts and 
bolts and the torque check. The average labor rate is $65 per work 
hour. Based on these figures, the cost impact of the AD on U.S. 
operators is estimated to be $2,730, or $65 per airplane, per 
inspection and torque check.
    It will take approximately 3 work hours per airplane to accomplish 
the required detailed inspection of the aft trunnion bearing cap. The 
average labor rate is $65 per airplane. Based on these figures, the 
cost impact on U.S. operators is estimated to be $8,190, or $195 per 
airplane.
    It will take approximately 4 work hours per airplane to accomplish 
the required installation of the new Inconel barrel nut and bolt and 
the main landing gear trunnion. The average labor rate is $65 per work 
hour. Based on these figures, the cost on U.S. operators is estimated 
to be $10,920, or $260 per airplane.
    Required parts will cost approximately $3,380 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. 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

[[Page 17926]]

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:

2004-07-06 Boeing: Amendment 39-13550. Docket 2002-NM-335-AD.

    Applicability: Model 707 and 720 series airplanes, as listed in 
Boeing 707 Alert Service Bulletin A3509, dated June 13, 2002; 
certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct cracking and/or loss of the upper and 
lower barrel nuts and bolts that retain the aft trunnion support 
fitting, which could result in the collapse of the main landing gear 
upon landing, accomplish the following:

Service Bulletin References

    (a) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of Boeing 707 Alert Service Bulletin 
A3509, dated June 13, 2002.

Initial Inspection

    (b) Within 60 days after the effective date of this AD, for each 
main landing gear, perform the inspection specified in paragraph 
(b)(1) of this AD and the torque check specified in paragraph (b)(2) 
of this AD, in accordance with the service bulletin.
    (1) Perform a detailed inspection of the upper and lower barrel 
nuts and bolts that retain the aft trunnion support fitting for 
corrosion, cracks, and loose or missing nuts and bolts.
    (2) Torque check the upper and lower bolts to verify the torque 
is within the range specified in Figure 2 of the service bulletin.

Repetitive Inspections

    (c) If no corrosion, crack, or loose or missing nut or bolt is 
found, and the torque is found to be within the specified range, 
during the inspection and torque check specified in paragraph (b) of 
this AD, then repeat the actions specified in paragraph (b) of this 
AD thereafter at intervals not to exceed 60 days.

Corrective Actions

    (d) If any corrosion, crack, or loose or missing nut or bolt is 
found, or if the torque is found not to be within the specified 
range, during the inspection and torque check specified in paragraph 
(b) of this AD: Before further flight, do the corrective actions 
specified in paragraphs (d)(1) through (d)(3) of this AD. 
Accomplishment of these actions constitutes terminating action for 
the repetitive inspections specified in paragraph (c) of this AD.
    (1) Perform a detailed inspection of the aft trunnion bearing 
cap and aft trunnion support fitting for corrosion, in accordance 
with the service bulletin. If any corrosion is detected, before 
further flight, repair in accordance with the service bulletin.
    (2) Perform a magnetic particle inspection of the aft trunnion 
bearing cap for cracks in accordance with Figure 3 of the service 
bulletin.
    (i) If no crack is found, before further flight, reinstall the 
inspected aft trunnion bearing cap in accordance with the service 
bulletin.
    (ii) If any crack is found, before further flight, replace the 
aft trunnion bearing cap with a new aft trunnion bearing cap in 
accordance with the service bulletin.
    (3) Reinstall the main landing gear trunnion with new Inconel 
barrel nuts and bolts to retain the aft trunnion support fitting, in 
accordance with Figure 4 of the service bulletin.

Terminating Action

    (e) Within one year after the effective date of this AD, for 
each main landing gear, replace the upper and lower steel barrel 
nuts and H-11 bolts that retain the aft trunnion support fitting 
with new Inconel barrel nuts and bolts as specified in paragraphs 
(d)(1) through (d)(3) of this AD. Accomplishment of these actions 
constitutes terminating action for the requirements of this AD.

Parts Installation

    (f) As of the effective date of this AD, no person shall install 
a steel barrel nut with H-11 bolt to retain the aft trunnion support 
fitting, on any airplane.

Alternative Methods of Compliance

    (g) In accordance with 14 CFR 39.19, the Manager, Seattle 
Aircraft Certification Office, FAA, is authorized to approve 
alternative methods of compliance for this AD.

Incorporation by Reference

    (h) The actions shall be done in accordance with Boeing 707 
Alert Service Bulletin A3509, dated June 13, 2002. 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 Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (i) This amendment becomes effective on May 11, 2004.


    Issued in Renton, Washington, on March 19, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-7126 Filed 4-5-04; 8:45 am]
BILLING CODE 4910-13-P

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