Airworthiness Directives; Lockheed Model 382, 382B, 382E, 382F, 382G, and 382J Series Airplanes, 38311-38313 [E8-15181]

Download as PDF pwalker on PROD1PC71 with RULES Federal Register / Vol. 73, No. 130 / Monday, July 7, 2008 / Rules and Regulations incurred by small handlers that are not incurred by large handlers. While the level of benefits of this rulemaking are difficult to quantify, the stabilizing effects of the volume regulations impact small and large handlers positively by helping them maintain and expand markets even though raisin supplies fluctuate widely from season to season. Likewise, price stability positively impacts small and large producers by allowing them to better anticipate the revenues their raisins will generate. AMS is committed to complying with the E-Government Act, to promote the use of the Internet and other information technologies to provide increased opportunities for citizen access to Government information and services, and for other purposes. There are some reporting, recordkeeping and other compliance requirements under the order. The reporting and recordkeeping requirements are necessary for compliance purposes and for developing statistical data for maintenance of the program. The requirements are the same as those applied in past seasons. Thus, this action imposes no additional reporting or recordkeeping requirements on either small or large raisin handlers. The forms require information which is readily available from handler records and which can be provided without data processing equipment or trained statistical staff. The information collection and recordkeeping requirements have been previously approved by the Office of Management and Budget (OMB) under OMB No. 0581–0178, Vegetable and Specialty Crops. As with all Federal marketing order programs, reports and forms are periodically reviewed to reduce information requirements and duplication by industry and public sector agencies. In addition, as noted in the initial regulatory flexibility analysis, USDA has not identified any relevant Federal rules that duplicate, overlap, or conflict with this rule. Further, the Committee’s meetings were widely publicized throughout the raisin industry and all interested persons were invited to attend the meetings and participate in the Committee’s deliberations. Like all Committee meetings, the August 14, 2007, October 4, 2007, and October 11, 2007, meetings were public meetings and all entities, both large and small, were able to express their views on this issue. Also, the Committee has a number of appointed subcommittees to review certain issues and make recommendations to the Committee. VerDate Aug<31>2005 16:13 Jul 03, 2008 Jkt 214001 The Committee’s Reserve Sales and Marketing Subcommittee met on August 14, 2007, and October 4, 2007, and discussed these issues in detail. Those meetings were also public meetings and both large and small entities were able to participate and express their views. An interim final rule concerning this action was published in the Federal Register on February 19, 2008. Copies of the rule were mailed by the Committee’s staff to all Committee members and alternates and raisin handlers. In addition, the rule was made available through the Internet by USDA and the Office of the Federal Register. That rule provided a 60-day comment period which ended April 21, 2008. No comments were received during the comment period. A small business guide on complying with fruit, vegetable, and specialty crop marketing agreements and orders may be viewed at: http://www.ams.usda.gov/ AMSv1.0/ams.fetchTemplateData.do? template=TemplateN &page=MarketingOrdersSmallBusiness Guide. Any questions about the compliance guide should be sent to Jay Guerber at the previously mentioned address in the FOR FURTHER INFORMATION CONTACT section. After consideration of all relevant material presented, including the Committee’s recommendation, and other information, it is found that finalizing the interim final rule, without change, as published in the Federal Register (73 FR 9005, February 19, 2008) will tend to effectuate the declared policy of the Act. List of Subjects in 7 CFR Part 989 Grapes, Marketing agreements, Raisins, Reporting and recordkeeping requirements. PART 989—RAISINS PRODUCED FROM GRAPES GROWN IN CALIFORNIA Accordingly, the interim final rule amending 7 CFR part 989 which was published at 73 FR 9005 on February 19, 2008, is adopted as a final rule without change. I Dated: July 1, 2008. Lloyd C. Day, Administrator, Agricultural Marketing Service. [FR Doc. E8–15293 Filed 7–3–08; 8:45 am] BILLING CODE 3410–02–P PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 38311 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 Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: 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 E:\FR\FM\07JYR1.SGM 07JYR1 38312 Federal Register / Vol. 73, No. 130 / Monday, July 7, 2008 / Rules and Regulations 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. pwalker on PROD1PC71 with RULES 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 VerDate Aug<31>2005 16:13 Jul 03, 2008 Jkt 214001 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. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 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 Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. E:\FR\FM\07JYR1.SGM 07JYR1 Federal Register / Vol. 73, No. 130 / Monday, July 7, 2008 / Rules and Regulations § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: I 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. pwalker on PROD1PC71 with RULES 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 VerDate Aug<31>2005 16:13 Jul 03, 2008 Jkt 214001 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 ‘‘NOLOADING’’ 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 footpounds (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 PO 00000 (j) None. Frm 00007 Fmt 4700 Sfmt 4700 38313 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] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2008–0683; Airspace Docket No. 08–ASW–11] Establishment of Class E Airspace; Plains, TX Federal Aviation Administration (FAA), DOT. ACTION: Direct final rule; request for comments. AGENCY: SUMMARY: This action establishes Class E5 airspace at Plains, TX. Additional controlled airspace is necessary to accommodate aircraft using new RNAV Global Positioning System (GPS) Standard Instrument Approach Procedures (SIAP) at Yoakum County Airport, Plains, TX. This action will enhance the safety and management of Instrument Flight Rules (IFR) aircraft operations at Yoakum County Airport. DATES: Effective Date: 0901 UTC September 25, 2008. Comments for inclusion in the rules Docket must be received August 21, 2008. The Director of the Federal Register approves this incorporation by reference action under Title 1, Code of Federal Regulations, part 51, subject to the annual revision of FAA Order 7400.9 and publication of conforming amendments. ADDRESSES: Send comments on this proposal to the U.S. Department of Transportation, Docket Operations, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. You must identify the docket number FAA–2008– 0683/Airspace Docket No. 08–ASW–11, at the beginning of your comments. You may also submit comments through the Internet at http://regulations.gov. You may review the public docket containing the proposal, any comments received, and any final disposition in person in the Dockets Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone 1–800–647– 5527) is on the ground floor of the building at the above address. FOR FURTHER INFORMATION CONTACT: Gary A. Mallett, Central Service Center, Operations Support Group, Federal E:\FR\FM\07JYR1.SGM 07JYR1

Agencies

[Federal Register Volume 73, Number 130 (Monday, July 7, 2008)]
[Rules and Regulations]
[Pages 38311-38313]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-15181]


=======================================================================
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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.

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

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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