Document ID: FAA-2008-0740-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Lockheed Model 382, 382B, 382E, 382F, 382G, and 382J Series Airplanes
Posted Date: 2008-07-07T04:00Z

[Federal Register: July 7, 2008 (Volume 73, Number 130)]
[Rules and Regulations]               
[Page 38311-38313]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr07jy08-2]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0740; Directorate Identifier 2008-NM-077-AD; 
Amendment 39-15605; AD 2008-14-10]
RIN 2120-AA64

 
Airworthiness Directives; Lockheed Model 382, 382B, 382E, 382F, 
382G, and 382J Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Lockheed Model 382, 382B, 382E, 382F, 382G, and 382J series airplanes. 
This AD requires, among other actions, an inspection to determine 
whether a certain upper engine mount bolt is installed, and replacement 
of any discrepant upper engine mount bolt with a new one. This AD 
results from a report indicating that several upper engine mount bolts 
manufactured by a certain supplier broke during installation. We are 
issuing this AD to prevent failure of the upper engine mount bolts, 
which could result in reduced structural capability of an engine mount, 
and possible separation of a strut and engine from the airplane during 
flight.

DATES: This AD is effective July 22, 2008.
    We must receive comments on this AD by September 5, 2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through

[[Page 38312]]

Friday, except Federal holidays. The AD docket contains this AD, the 
regulatory evaluation, any comments received, and other information. 
The street address for the Docket Office (telephone 800-647-5527) is in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Carl Gray, Aerospace Engineer, 
Airframe Branch, ACE-117A, FAA, Atlanta Aircraft Certification Office, 
One Crown Center, 1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia 
30349; telephone (770) 703-6131; fax (770) 703-6097.

SUPPLEMENTARY INFORMATION:

Discussion

    We have received a report indicating that several upper engine 
mount bolts broke during installation. These bolts have part number (P/
N) NAS 636 and have ``AFC'' or ``A'' (AirFasco of Canton, Ohio) stamped 
on the bolt head. Upper engine mount bolts are used to attach the quick 
engine change (QEC) to the truss mounts in a four-bolt pattern (two 
upper and two lower bolts). The failures occurred on military versions 
of Lockheed Model 382, 382B, 382E, 382F, 382G, and 382J series 
airplanes. The discrepant bolts were located in the upper two positions 
of the four bolt pattern (different bolts are installed in the lower 
two positions and are not interchangeable with the bolts in the upper 
two positions). Investigation revealed that Lockheed has not approved 
AirFasco as a supplier of these bolts. Material hardness testing also 
revealed that the discrepant bolts do not meet hardness requirements. 
The cause for the inadequate hardness is improper heat treatment.
    Failure of the upper engine mount bolts could result in reduced 
structural capability of an engine mount, and possible separation of a 
strut and engine from the airplane during flight.
    The upper engine mount bolts are commercially available. We do not 
know whether any of the discrepant bolts were sold to commercial 
operators by the supplier or an agent. Therefore, the discrepant bolts 
might be installed on Lockheed Model 382, 382B, 382E, 382F, 382G, and 
382J series airplanes.

FAA's Determination and Requirements of This AD

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the(se) same type 
design(s). This AD requires, among other actions, an inspection to 
determine whether a certain upper engine mount bolt is installed, and 
replacement of any discrepant upper engine mount bolt with a new one.

FAA's Justification and Determination of the Effective Date

    It is not known when or if the discrepant upper engine mount bolts 
might have been installed on affected airplanes. The QEC-to-truss mount 
joint is designed to be failsafe for a single failed upper engine mount 
bolt. If both bolts in the upper position of an upper engine mount are 
discrepant, the ability for this joint to carry the QEC loads is 
compromised, and consequently one upper engine mount bolt could fail. 
If one bolt in the upper position of an upper engine mount fails, the 
other bolt in the upper position of the upper engine mount could also 
fail within a short amount of time. Failure to replace these discrepant 
bolts greatly increases the risk of operating with a QEC attachment 
system that might be incapable of handling design level loads. Because 
of our requirement to promote safe flight of civil aircraft and the 
critical need to ensure the structural capability of an engine mount 
and the short compliance time involved with this action, this AD must 
be issued immediately.
    Because an unsafe condition exists that requires the immediate 
adoption of this AD, we find that notice and opportunity for prior 
public comment hereon are impracticable and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments before it becomes effective. However, we invite 
you to send any written data, views, or arguments about this AD. Send 
your comments to an address listed under the ADDRESSES section. Include 
``Docket No. FAA-2008-0740; Directorate Identifier 2008-NM-077-AD'' at 
the beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of this 
AD. We will consider all comments received by the closing date and may 
amend this AD because of those comments.
    We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

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

    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 that this AD:
    (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.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 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.

[[Page 38313]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2008-14-10 Lockheed: Amendment 39-15605. Docket No. FAA-2008-0740; 
Directorate Identifier 2008-NM-077-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective July 22, 
2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Lockheed Model 382, 382B, 382E, 382F, 
382G, and 382J series airplanes, certificated in any category.

Unsafe Condition

    (d) This AD results from a report indicating that several upper 
engine mount bolts manufactured by a certain supplier broke during 
installation. We are issuing this AD to prevent failure of the upper 
engine mount bolts, which could result in reduced structural 
capability of an engine mount, and possible separation of a strut 
and engine from the airplane during flight.

Compliance

    (e) Comply with this AD within the compliance times specified, 
unless already done.

Access and Inspection

    (f) Within 10 days after the effective date of this AD do the 
actions specified in paragraphs (f)(1), (f)(2), and (f)(3) of this 
AD.
    (1) Make the airplane safe for maintenance in accordance with a 
method approved by the Manager, Atlanta Aircraft Certification 
Office (ACO), FAA. Chapter 71-00 of the Lockheed Hercules 
Maintenance Manual is one approved method.
    (2) Gain access to the upper engine mount bolts by opening the 
left and right cowling doors on each engine.
    (3) Inspect the visible surface head of each bolt in the upper 
position of each upper engine mount to determine whether part number 
(P/N) ``NAS 636'' is stamped across the top, and whether the 
manufacturer's code ``AFC'' or ``A'' (i.e., AirFasco) is stamped 
across the bottom. All other manufacturers' codes are acceptable.

Replacement and Corrective Actions

    (g) If any upper position bolt, P/N NAS 636, having ``AFC'' or 
``A'' stamped across the bottom of the surface head is found during 
the inspection required by paragraph (f)(3) of this AD, before 
further flight, replace that bolt with a new bolt, P/N NAS 636, 
having a manufacturers' code other than ``AFC'' or ``A,'' in 
accordance with a method approved by the Manager, Atlanta ACO, FAA. 
One approved method is the following: To replace an engine mount 
bolt without removing an engine, do the actions specified in 
paragraphs (g)(1) through (g)(8) of this AD. If both bolts in the 
upper position of an engine mount must be replaced, the replacements 
must be done one at a time to prevent alignment problems.
    (1) Shut down and disconnect external electrical power in 
accordance with a method approved by the Manager, Atlanta ACO, FAA. 
Chapter 24-40 of the Lockheed Hercules Maintenance Manual is one 
approved method.
    (2) Attach a warning tag and close the external power receptacle 
door.
    (3) Install the nacelle hoist sling on the power package.
    (4) Lift the nacelle hoist sling enough to take up load. 
Warning: When ``NO-LOADING'' an engine with the sling, the intention 
is to transfer most of the weight of the engine from the airplane to 
the sling. This requires some judgment on the part of the 
technician. Under no circumstances should the sling be raised enough 
to lift the airplane.
    (5) Remove the discrepant upper engine mount bolt and washer.
    (6) Install the new upper engine mount bolt, P/N NAS 636, having 
a manufacturers' code other than ``AFC'' or ``A,'' and washer, and 
torque to between 308 and 458 foot-pounds (3,700 to 5,500 inch-
pounds).
    (7) Remove the nacelle hoist sling from the power package.
    (8) Once all discrepant bolts in the upper position of each 
upper engine mount have been replaced, restore the airplane to 
service in accordance with a method approved by the Manager, Atlanta 
ACO, FAA. Chapter 71-00 of the Lockheed Hercules Maintenance Manual 
is one approved method.

    Note 1: It is the intent of the actions specified in paragraph 
(g) of this AD to allow replacement of individual upper engine mount 
bolts without having to do any other maintenance.

Parts Installation

    (h) As of the effective date of this AD, no person may install a 
bolt, P/N NAS 636, having ``AFC'' or ``A'' stamped across the bottom 
of the surface head, in the upper position of any upper engine 
mount, on any airplane.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, Atlanta ACO, FAA, ATTN: Carl Gray, Aerospace 
Engineer, Airframe Branch, ACE-117A, FAA, Atlanta ACO, One Crown 
Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; 
telephone (770) 703-6131; fax (770) 703-6097; has the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
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.

Material Incorporated by Reference

    (j) None.

    Issued in Renton, Washington, on June 24, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-15181 Filed 7-3-08; 8:45 am]

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