42262 Federal Register / Vol. 70, No. 140 / Friday, July 22, 2005 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 99–NM–129–AD; Amendment 

39–14190; AD 2005–15–01] 

RIN 2120–AA64 

Airworthiness Directives; Lockheed 

Model L–1011–385 Series Airplanes

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT).

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to all Lockheed Model L–

1011–385 series airplanes, that requires 

repetitive inspections to detect 

corrosion or fatigue cracking of certain 

structural elements of the airplane; 

corrective actions if necessary; and 

incorporation of certain structural 

modifications. This action is necessary 

to prevent corrosion or fatigue cracking 

of certain structural elements, which 

could result in reduced structural 

integrity of the airplane. This action is 

intended to address the identified 

unsafe condition.

DATES: Effective August 26, 2005. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of August 26, 

2005.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Lockheed Martin Aircraft & 

Logistics Centers, 120 Orion Street, 

Greenville, South Carolina 29605. 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 FAA, 

Atlanta Aircraft Certification Office, 

One Crown Center, 1895 Phoenix 

Boulevard, suite 450, Atlanta, Georgia.

FOR FURTHER INFORMATION CONTACT:

William Herderich, Aerospace Engineer, 

Airframe Branch, ACE–117A, FAA, 

Atlanta Aircraft Certification Office, 

One Crown Center, 1895 Phoenix 

Boulevard, suite 450, Atlanta, Georgia 

30349; telephone (770) 703–6082; fax 

(770) 703–6097.

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 all Lockheed Model 

L–1011–385 series airplanes was 

published as a supplemental notice of 

proposed rulemaking (NPRM) in the 

Federal Register on December 16, 2004 

(69 FR 75282). That action proposed to 

require repetitive inspections to detect 

corrosion or fatigue cracking of certain 

structural elements of the airplane; 

corrective actions if necessary; and 

incorporation of certain structural 

modifications. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

comments received. 

Request To Separate Service Bulletins 

into Two Tables 

One commenter requests that Table 

1—Compliance Times be split into two 

tables—an inspection table (Table I) and 

an inspection/modification table (Table 

II)—similar to that in Lockheed Tristar 

L–1011 Service Bulletin 093–51–041, 

Revision 1, dated March 3, 2000 

(referenced in the supplemental NPRM 

as an appropriate source of service 

information; hereafter called the 

‘‘Collector Service Bulletin’’). The 

commenter believes that Table 1 of the 

supplemental NPRM implies that all 

listed service bulletins have a 

terminating modification, which would 

cause confusion. Whereas Table I lists 

service bulletins with no terminating 

action in most cases, and Table II lists 

service bulletins with terminating 

actions. 

We partially agree. We do not agree 

that Table 1 of the AD should be split 

into two tables. As explained in the 

preamble of the supplemental NPRM, 

we revised the original NPRM by adding 

Table 1 for the sole purpose of listing 

the compliance times for each 

individual service bulletin listed in 

Tables I and II of the referenced 

Lockheed service bulletin. We made this 

change based on commenters’ requests 

to clarify the compliance times. We 

agree with the commenter that operators 

could misinterpret that all service 

bulletins listed in Table 1 have a 

terminating modification. Therefore, we 

have revised Table 1 of the AD by 

adding a new column ‘‘Terminating 

Action’’ to identify service bulletins that 

have a terminating modification. 

Request To Include Revision Level of 

Service Bulletin 

One commenter notes that the service 

bulletin date (i.e., 093–53–054, dated 

August 12, 1975) identified in paragraph 

(a)(8) of the supplemental NPRM 

corresponds to Revision 1 of the service 

bulletin, not the original issue as 

indicated. 

From this comment, we infer that the 

commenter is requesting clarification. 

The commenter is correct that the 

service bulletin reference should have 

included ‘‘Revision 1.’’ We have revised 

paragraph (a)(8) of the final rule 

accordingly. 

Conclusion 

After careful review of the available 

data, including the comments noted 

above, the FAA has determined that air 

safety and the public interest require the 

adoption of the rule with the change 

previously described. The FAA has 

determined that this change will neither 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Changes to 14 CFR Part 39/Effect on the 

AD 

On July 10, 2002, the FAA issued a 

new version of 14 CFR part 39 (67 FR 

47997, July 22, 2002), which governs the 

FAA’s airworthiness directives system. 

The regulation now includes material 

that relates to altered products, special 

flight permits, and alternative methods 

of compliance. However, for clarity and 

consistency in this final rule, we have 

retained the language of the 

supplemental NPRM regarding that 

material.

Cost Impact 

There are approximately 125 

airplanes of the affected design in the 

worldwide fleet. The FAA estimates that 

49 airplanes (7 in-service and 42 in 

storage) of U.S. registry will be affected 

by this AD. Few, if any of the 42 

airplanes in storage, will be returned to 

service due to the economic feasbility of 

operating and maintaining older 

technology airplanes. Therefore, the cost 

estimate below is based on the 7 inservice airplanes. 

It will take approximately 32 work 

hours per airplane (for actions specified 

in Table I of the Collector Service 

Bulletin) and 97 work hours per 

airplane (for actions specified in Table 

II of the Collector Service Bulletin) to 

accomplish the required inspections, at 

an average labor rate of $65 per work 

hour. Based on these figures, the cost 

impact of the AD on U.S. operators is 

estimated to be $14,560, or $2,080 per 

airplane, per inspection cycle (for Table 

I), and $44,135, or $6,305 per airplane, 

per inspection cycle (for Table II). 

It will take approximately 614 work 

hours per airplane to accomplish the 

required modifications, at an average 

labor rate is $65 per work hour. 

Required parts will cost approximately 

$142,275 per airplane. Based on these 

figures, the cost impact of the proposed 

Federal Register / Vol. 70, No. 140 / Friday, July 22, 2005 / Rules and Regulations 42263

AD on U.S. operators is estimated to be 

$1,275,295, or $182,185 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. 

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 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

■ 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.

§ 39.13 [Amended]

■ 2. Section 39.13 is amended by adding 

the following new airworthiness 

directive:

2005–15–01 Lockheed: Amendment 39–

14190. Docket 99–NM–129–AD.

Applicability: All Model L–1011–385 

series airplanes, 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 (d) 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 corrosion or fatigue cracking of 

certain structural elements, which could 

result in reduced structural integrity of the 

airplane, accomplish the following: 

Inspections 

(a) At the time specified in the ‘‘Initial 

Compliance Time’’ column of Table 1 of this 

AD, perform structural inspections to detect 

corrosion or fatigue cracking of certain 

structural elements of the airplane, in 

accordance with the applicable service 

bulletins listed under ‘‘Service Bulletin 

Number, Revision, and Date’’ in Tables I and 

II of Lockheed Tristar L–1011 Service 

Bulletin 093–51–041, Revision 1, dated 

March 3, 2000. Thereafter, repeat the 

inspections at intervals specified in the 

‘‘Repetitive Intervals’’ column of Table 1 of 

this AD.

TABLE 1.—COMPLIANCE TIMES

Lockheed TriStar L–1011 

service bulletin 

Initial compliance time (whichever occurs later between 

the times in ‘‘inspection threshold’’ and ‘‘grace period’’) Repetitive

intervals 

Terminating

action 

Inspection threshold Grace period 

(1) 093–53–269, Revision 

1, dated October 28, 

1997.

Before the accumulation of 

8,000 total flight cycles 

or 15,000 total flight 

hours, whichever occurs 

first.

Within 6,450 flight cycles 

or 5 years after the effective date of this AD, 

whichever occurs first.

At intervals not to exceed 

6,450 flight cycles or 5 

years, whichever occurs 

first.

(None). 

(2) 093–53–274, dated 

May 28, 1997.

Within 14 months after the 

effective date of this AD.

(None) ............................... At intervals not to exceed 

14 months.

(None). 

(3) 093–53–275, dated December 10, 1996.Within 6,450 flight cycles 

or 5 years after the effective date of this AD, 

whichever occurs first.

(None) ............................... (None) ............................... (None). 

(4) 093–53–276, dated 

June 17, 1996.

At the next Corrosion Prevention and Control Program (CPCP) inspection 

after the effective date 

of this AD.

(None) ............................... At intervals not to exceed 

the next CPCP inspection.

(None). 

42264 Federal Register / Vol. 70, No. 140 / Friday, July 22, 2005 / Rules and Regulations 

TABLE 1.—COMPLIANCE TIMES—Continued

Lockheed TriStar L–1011 

service bulletin 

Initial compliance time (whichever occurs later between 

the times in ‘‘inspection threshold’’ and ‘‘grace period’’) Repetitive

intervals 

Terminating

action 

Inspection threshold Grace period 

(5) 093–57–085, Revision 

1, dated December 1, 

1997.

Before the accumulation of 

26,000 total flight cycles 

or 48,000 total flight 

hours, whichever occurs 

first.

Within 1,800 flight cycles 

or 3,300 flight hours 

after the effective date 

of this AD, whichever 

occurs first.

At intervals not to exceed 

1,800 flight cycles or 

3,300 flight hours, 

whichever occurs first.

Modification in accordance 

with Lockheed TriStar 

L–1011 Service Bulletin 

093–57–085, Basic 

Issue, dated May 7, 

1993; or Revision 1, 

dated December 1, 

1997. 

(6) 093–57–208, Revision 

1, dated October 28, 

1997.

Before the accumulation of 

18,000 total flight cycles.

Within 6,450 flight cycles 

or 5 years after the effective date of this AD, 

whichever occurs first.

At intervals not to exceed 

6,450 flight cycles or 5 

years, whichever occurs 

first.

(None). 

(7) 093–52–210, dated 

July 19, 1991.

Within 5,000 flight hours or 

18 months after the effective date of this AD, 

whichever occurs first.

(None) ............................... (None) ............................... (None). 

(8) 093–53–054, Revision 

1, dated August 12, 

1975.

Within 6,450 flight cycles 

or 5 years after the effective date of this AD, 

whichever occurs first.

(None) ............................... (None) ............................... (None). 

(9) 093–53–070, Revision 

3, dated September 19, 

1989.

Before the accumulation of 

6,000 total flight hours.

Within 1,500 flight hours 

after the effective date 

of this AD.

At intervals not to exceed 

3,000 flight hours.

Modification in accordance 

with Lockheed TriStar 

L–1011 Service Bulletin 

093–53–070, Basic 

Issue, dated September 

26, 1974; Revision 1, 

dated January 23, 1975; 

Revision 2, dated July 7, 

1975; or Revision 3, 

dated September 19, 

1989. 

(10) 093–53– 085, Revision 3, dated December 

15, 1989.

Part I: Before the accumulation of 20,000 flight cycles or 37,000 total flight 

hours, whichever occurs 

first.

Part I: Within 1,600 flight 

cycles or 3,000 flight 

hours after the effective 

date of this AD, whichever occurs first.

Part I: At intervals not to 

exceed 1,600 flight cycles or 3,000 flight 

hours, whichever occurs 

first.

Modification in accordance 

with Lockheed TriStar 

L–1011 Service Bulletin 

093–53–085, Basic 

Issue, dated September 

29, 1975; Revision 1, 

dated September 3, 

1976; or Revision 2, 

dated February 8, 1988. 

Part II: Before the accumulation of 30,000 flight cycles or 55,000 total flight 

hours, whichever occurs 

first.

Part II: Within 5,000 flight 

cycles or 9,200 flight 

hours after the effective 

date of this AD, whichever occurs first.

Part II: At intervals not to 

exceed 5,000 flight cycles or 9,200 flight 

hours, whichever occurs 

first.

Modification in accordance 

with Lockheed TriStar 

L–1011 Service Bulletin 

093–53–085, Basic 

Issue, dated September 

29, 1975; Revision 1, 

dated September 3, 

1976; or Revision 2, 

dated February 8, 1988. 

(11) 093–53– 086, Revision 5, dated April 12, 

1990.

Before the accumulation of 

9,000 flight cycles or 

10,000 flight hours, 

whichever occurs first.

Within 1,600 flight cycles 

or 3,000 flight hours 

after the effective date 

of this AD, whichever 

occurs first.

At intervals not to exceed 

1,600 flight cycles or 

3,000 flight hours, 

whichever occurs first.

Modification in accordance 

with Lockheed TriStar 

L–1011 Service Bulletin 

093–53–086, Basic 

Issue, dated September 

26, 1975; Revision 1, 

dated November 12, 

1975; Revision 2, dated 

December 12, 1976; Revision 3, dated July 19, 

1977; Revision 4, dated 

July 8, 1985; or Revision 

5, dated April 12, 1990. 

(12) 093–53–110, Revision 

1, dated May 7, 1993.

Before the accumulation of 

22,000 total flight cycles 

or 40,000 total flight 

hours, whichever occurs 

first.

Within 2,200 flight cycles 

or 4,000 flight hours 

after the effective date 

of this AD, whichever 

occurs first.

At intervals not to exceed 

2,200 flight cycles or 

4,000 flight hours, 

whichever occurs first.

Modification in accordance 

with Lockheed TriStar 

L–1011 Service Bulletin 

093–53–110, Basic 

Issue, dated August 19, 

1991; or Revision 1, 

dated May 7, 1993. 

Federal Register / Vol. 70, No. 140 / Friday, July 22, 2005 / Rules and Regulations 42265

TABLE 1.—COMPLIANCE TIMES—Continued

Lockheed TriStar L–1011 

service bulletin 

Initial compliance time (whichever occurs later between 

the times in ‘‘inspection threshold’’ and ‘‘grace period’’) Repetitive

intervals 

Terminating

action 

Inspection threshold Grace period 

(13) Change Notification 

093–53–260, CN4, dated 

May 8, 1998.

Before the accumulation of 

8,000 total flight cycles 

or 20,000 total flight 

hours, whichever occurs 

first.

Within 800 flight cycles or 

1,500 flight hours after 

the effective date of this 

AD, whichever occurs 

first.

At intervals not to exceed 

800 flight cycles or 

1,500 flight hours, 

whichever occurs first.

Inspection and modification in accordance with 

Part 2.A. of Lockheed 

TriStar L–1011 Service 

Bulletin 093–53–260, 

Basic Issue, dated May 

15, 1991. 

(14) Change Notification 

093–53–266, CN1, dated 

July 10, 1992.

Within 12 months after the 

effective date of this AD.

(None) ............................... At intervals not to exceed 

90 days.

Modification in accordance 

with Lockheed TriStar 

L–1011 Service Bulletin 

093–53–266, Basic 

Issue, dated March 2, 

1992. 

(15) Change Notification 

093–57–058, R5–CN1, 

dated May 3, 1993.

Before the accumulation of 

20,000 total flight cycles 

or 37,000 total flight cycles or 37,000 total flight 

hours, whichever occurs 

first.

Within 1,600 flight cycles 

or 3,000 flight hours 

after the effective date 

of this AD, whichever 

occurs first.

At intervals not to exceed 

1,600 flight cycles or 

3,000 flight hours, 

whichever occurs first.

Modification in accordance 

with Lockheed TriStar 

L–1011 Service Bulletin 

093–57–058, Basic 

Issue, dated September 

16, 1975; Revision 1, 

dated December 1, 

1976; Revision 2, dated 

June 30, 1978; Revision 

3, dated October 19, 

1978; or Revision 4, 

dated July 6, 1981, Revision 5, dated June 9, 

1983. 

(16) Change Notification 

093–57–195, R3–CN1, 

dated August 22, 1995.

For airplanes having serial 

numbers (S/N) 1002 

through 1109 inclusive: 

Before the accumulation 

of 20,000 total flight cycles.

Within 2,200 flight cycles 

after the effective date 

of this AD.

At intervals not to exceed 

2,200 flight cycles.

Modification in accordance 

with Lockheed TriStar 

L–1011 Service Bulletin 

093–57–195, Revision 2, 

dated July 27, 1990; or 

Revision 3, dated June 

30, 1992. 

For airplanes having S/Ns 

1110 through 1250 inclusive: Before the accumulation of 30,000 total 

flight cycles.

(17) Change Notification 

093–57–213, CN1, dated 

February 20, 1996.

For Model L–1011–385–1, 

L–1011–385–1–14, L–

1011–385–1–15: Before 

the accumulation of 

15,000 total flight cycles.

Within 6,450 flight cycles 

or 5 years after the effective date of this AD, 

whichever occurs first.

At intervals not to exceed 

6,450 flight cycles or 5 

years, whichever occurs 

first.

Repair or modification in 

accordance with Lockheed TriStar L–1011 

Service Bulletin 093–57–

213, Basic Issue, dated 

December 9, 1994. 

For Model L–1011–385–3: 

Before the accumulation 

of 10,000 total flight cycles.

Corrective Action 

(b) If any cracking or corrosion is detected 

during any inspection required by paragraph 

(a) of this AD, prior to further flight, 

accomplish the actions specified in 

paragraph (b)(1), (b)(2), (b)(3), or (b)(4) of this 

AD. 

(1) Repair in accordance with the 

applicable service bulletin referenced in 

Table I or II of Lockheed Tristar L–1011 

Service Bulletin 093–51–041, Revision 1, 

dated March 3, 2000.

(2) Repair in accordance with the 

applicable section of the Lockheed L–1011 

Structural Repair Manual. 

(3) Accomplish the terminating 

modification in accordance with the 

applicable service bulletin referenced in 

Table I or II of Lockheed Tristar L–1011 

Service Bulletin 093–51–041, Revision 1, 

dated March 3, 2000. 

(4) Repair in accordance with a method 

approved by the Manager, Atlanta Aircraft 

Certification Office (ACO), FAA. 

Terminating Action 

(c) Within 5 years or 5,000 flight cycles 

after the effective date of this AD, whichever 

occurs first, install the terminating 

modification referenced in the applicable 

service bulletin listed in Table 1 of this AD, 

per the applicable service bulletin. Such 

installation constitutes terminating action for 

the applicable structural inspection required 

by paragraph (a) of this AD. 

Alternative Methods of Compliance 

(d) 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, Atlanta 

ACO, FAA. Operators shall submit their 

requests through an appropriate FAA 

Principal Maintenance Inspector, who may 

add comments and then send it to the 

Manager, Atlanta ACO.

Note 2: Information concerning the 

existence of approved alternative methods of 

compliance with this AD, if any, may be 

obtained from the Atlanta ACO.

42266 Federal Register / Vol. 70, No. 140 / Friday, July 22, 2005 / Rules and Regulations 

Special Flight Permits 

(e) Special flight permits may be issued in 

accordance with sections 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 

(f) You must use the applicable service 

bulletins listed in Table 2 of this AD to 

perform the actions that are required by this 

AD, unless the AD specifies otherwise. 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 

Lockheed Martin Aircraft & Logistics Centers, 

120 Orion Street, Greenville, South Carolina 

29605. Copies may be inspected at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or at the 

FAA, Atlanta Aircraft Certification Office, 

One Crown Center, 1895 Phoenix Boulevard, 

suite 450, Atlanta, Georgia; 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.

TABLE 2.—MATERIAL INCORPORATED BY REFERENCE

Service bulletin Effective pages Revision level 

shown on page Date 

(1) Lockheed TriStar L–1011 Service Bulletin 093–51–041, Revision 1, dated March 3, 2000.1–13 ......................................... 1 ............................. March 3, 2000. 

(2) Lockheed TriStar L–1011 Service Bulletin 093–57–085, Revision 1, dated May 7, 1993.1–17 ......................................... Basic Issue ............ May 7, 1993. 

(3) Lockheed TriStar L–1011 Service Bulletin 093–57–085, Revision 1, dated December 1, 1997.1–7, 9, 10 ................................

8, 11–7 .....................................

1 .............................

Basic Issue ............

December 1, 1997. 

May 7, 1993. 

(4) Lockheed TriStar L–1011 Service Bulletin 093–53–070, 

Basic Issue, dated September 26, 1974.

1–15 ......................................... Basic Issue ............ September 26, 1974. 

(5) Lockheed TriStar L–1011 Service Bulletin 093–53–070, Revision 1, dated January 23, 1975.1, 4–7, 13–17 ..........................

2, 3, 8–12 ................................

1 .............................

Basic Issue ............

January 23, 1975. 

September 26, 1974. 

(6) Lockheed TriStar L–1011 Service Bulletin 093–53–070, Revision 2, dated July 7, 1975.1, 2, 7, 9–14 ............................

3, 8 ...........................................

4–6, 15–17 ...............................

2 .............................

Basic Issue ............

1 .............................

July 7, 1975. 

September 26, 1974. 

January 23, 1975. 

(7) Lockheed TriStar L–1011 Service Bulletin 093–53–070, Revision 3, dated September 19, 1989.1–6, 8–10 .................................

7 ...............................................

3 .............................

Basic Issue ............

September 19, 1989. 

September 26, 1974. 

(8) Lockheed TriStar L–1011 Service Bulletin 093–53–085, 

Basic Issue, dated September 29, 1975.

1–16 ......................................... Basic Issue ............ September 29, 1975. 

(9) Lockheed TriStar L–1011 Service Bulletin 093–53–085, Revision 1, dated September 3, 1976.1–3, 6, 9–11, 15 ......................

4, 5, 7, 8, 12–14, 16 ................

1 .............................

Basic Issue ............

September 3, 1976. 

September 29, 1975. 

(10) Lockheed TriStar L–1011 Service Bulletin 093–53–085, 

Revision 2, dated February 8, 1988.

1–23 ......................................... 2 ............................. February 8, 1988. 

(11) Lockheed TriStar L–1011 Service Bulletin 093–53–086, 

Basic Issue, dated September 26, 1975.

1–16 ......................................... Basic Issue ............ September 26, 1975. 

(12) Lockheed TriStar L–1011 Service Bulletin 093–53–086, 

Revision 1, dated November 12, 1975.

1, 2, 11, 15 ..............................

3–10, 12–14, 16 ......................

1 .............................

Basic Issue ............

November 12, 1975. 

September 26, 1975. 

(13) Lockheed TriStar L–1011 Service Bulletin 093–53–086, 

Revision 2, dated December 12, 1976.

1, 2, 7, 15, 16 ..........................

3–6, 8–10, 12–14 ....................

11 .............................................

2 .............................

Basic Issue ............

1 .............................

December 12, 1976. 

September 26, 1975. 

November 12, 1975. 

(14) Lockheed TriStar L–1011 Service Bulletin 093–53–086, 

Revision 3, dated July 19, 1977.

1, 2, 4, 7, 10, 11, 15 ................

3, 5, 6, 8, 9, 12–14 ..................

16 .............................................

3 .............................

Basic Issue ............

2 .............................

July 19, 1977. 

September 26, 1975. 

December 12, 1976. 

(15) Lockheed TriStar L–1011 Service Bulletin 093–53–086, 

Revision 4, dated July 8, 1985.

1–4, 15, 16 ..............................

5, 6, 8, 9, 12–14 ......................

7, 10, 11 ..................................

4 .............................

Basic Issue ............

3 .............................

July 8, 1985. 

Sepember 26, 1975. 

July 19, 1977. 

(16) Lockheed TriStar L–1011 Service Bulletin 093–53–086, 

Revision 5, dated April 12, 1990.

1–9, 13 .....................................

10–12 .......................................

14 .............................................

5 .............................

Basic Issue ............

4 .............................

April 12, 1990. 

September 26, 1975. 

July 8, 1985. 

(17) Lockheed TriStar L–1011 Service Bulletin 093–53–110, 

Basic Issue, dated August 19, 1991.

1–10 ......................................... Basic Issue ............ August 19, 1991. 

(18) Lockheed TriStar L–1011 Service Bulletin 093–53–110, 

Revision 1, dated May 7, 1993.

1–7, 9–12 .................................

8 ...............................................

1 .............................

Basic Issue ............

May 7, 1993. 

August 19, 1991. 

(19) Lockheed TriStar L–1011 Service Bulletin 093–53–260, 

Basic Issue, dated May 15, 1991.

1–26 ......................................... Basic Issue ............ May 15, 1991. 

(20) Lockheed TriStar L–1011 Service Bulletin 093–53–266, 

Basic Issue, dated March 2, 1992.

1–17 ......................................... Basic Issue ............ March 2, 1992. 

(21) Lockheed TriStar L–1011 Service Bulletin 093–57–058, 

Basic Issue, dated September 16, 1975.

1–19 ......................................... Basic Issue ............ September 16, 1975. 

(22) Lockheed TriStar L–1011 Service Bulletin 093–57–058, 

Revision 1, dated December 1, 1976.

1, 2, 4, 7, 8, 11, 15–19 ............

3, 5, 6, 9, 10, 12–14 ................

1 .............................

Basic Issue ............

December 1, 1976. 

September 16, 1975. 

(23) Lockheed TriStar L–1011 Service Bulletin 093–57–058, 

Revision 2, dated June 30, 1978.

1–4, 7, 8, 11, 15–19 ................

5, 6, 9, 10, 12–14 ....................

2 .............................

Basic Issue ............

June 30, 1978. 

September 16, 1975. 

(24) Lockheed TriStar L–1011 Service Bulletin 093–57–058, 

Revision 3, dated October 19, 1978.

1–3, 7, 8, 11, 15–19 ................

4 ...............................................

5, 6, 9, 10, 12–14 ....................

3 .............................

2 .............................

Basic Issue ............

October 19, 1978. 

June 30, 1978. 

September 16, 1975. 

(25) Lockheed TriStar L–1011 Service Bulletin 093–57–058, 

Revision 4, dated July 6, 1981.

1–3, 19 .....................................

4, 15 .........................................

5, 6, 9, 10, 12–14 ....................

7, 8, 11, 16–18 ........................

4 .............................

2 .............................

Basic Issue ............

3 .............................

July 6, 1981. 

June 30, 1978. 

September 16, 1975. 

October 19, 1978. 

Federal Register / Vol. 70, No. 140 / Friday, July 22, 2005 / Rules and Regulations 42267

TABLE 2.—MATERIAL INCORPORATED BY REFERENCE—Continued

Service bulletin Effective pages Revision level 

shown on page Date 

(26) Lockheed TriStar L–1011 Service Bulletin 093–57–058, 

Revision 5, dated June 9, 1983.

1, 3, 4, 7 ..................................

2 ...............................................

5, 6, 9, 10, 12–14 ....................

8, 11, 16–19 ............................

15 .............................................

5 .............................

4 .............................

Basic Issue ............

3 .............................

2 .............................

June 9, 1983. 

July 6, 1981. 

September 16, 1975. 

October 19, 1978. 

June 30, 1978. 

(27) Lockheed TriStar L–1011 Service Bulletin 093–53–070, 

Revision 2, dated July 27, 1990.

1–51 ......................................... 2 ............................. July 27, 1990. 

(28) Lockheed TriStar L–1011 Service Bulletin 093–53–070, 

Revision 3, dated June 30, 1992.

1–6, 23–28, 33, 34, 41, 42, 

45–52.

7–22, 29–32, 35–40, 43, 44 ....

3 .............................

2 .............................

June 30, 1992. 

July 27, 1990. 

(29) Lockheed TriStar L–1011 Service Bulletin 093–53–070, 

Basic Issue, dated December 9, 1994.

1–19 ......................................... Basic Issue ............ December 9, 1994. 

Effective Date 

(g) This amendment becomes effective on 

August 26, 2005.

Issued in Renton, Washington, on July 8, 

2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 05–14089 Filed 7–21–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–20867; Directorate 

Identifier 2004–NM–188–AD; Amendment 

39–14194; AD 2005–15–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

Series Airplanes, and Model A300 C4–

605R Variant F Airplanes (Collectively 

Called A300–600 Series Airplanes)

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT).

ACTION: Final rule.

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A300–600 series 

airplanes. This AD requires an 

inspection for evidence of chafing 

between the hydraulic flexible hose and 

the ram air turbine (RAT) hub, and 

related investigative and corrective 

actions if necessary. This AD is 

prompted by reports of holes in the RAT 

hub cover. We are issuing this AD to 

prevent a hole in the RAT hub cover. A 

hole in the RAT hub cover could allow 

water to enter the RAT governing 

mechanism, freeze during flight, and 

jam the governing mechanism. In 

addition, the metal particles that result 

from chafing between the hydraulic 

flexible hose and the RAT could mix 

with the lubricant grease and degrade 

the governing mechanism. In an 

emergency, a jammed or degraded RAT 

could result in its failure to deploy, loss 

of hydraulic pressure or electrical power 

to the airplane, and consequent reduced 

controllability of the airplane.

DATES: This AD becomes effective 

August 26, 2005. 

The incorporation by reference of a 

certain publication listed in the AD is 

approved by the Director of the Federal 

Register as of August 26, 2005.

ADDRESSES: For service information 

identified in this AD, contact Airbus, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France. 

Docket: The AD docket contains the 

proposed AD, comments, and any final 

disposition. You can examine the AD 

docket on the Internet at http://

dms.dot.gov, or in person at the Docket 

Management Facility office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The 

Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the U.S. Department of Transportation, 

400 Seventh Street SW., room PL–401, 

Washington, DC. This docket number is 

FAA–2005–20867; the directorate 

identifier for this docket is 2004–NM–

188–AD.

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington 

98055–4056; telephone (425) 227–2125; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

an AD for certain Airbus Model A300 

B4–600, B4–600R, and F4–600R series 

airplanes, and Model A300 C4–605R 

Variant F airplanes (collectively called 

A300–600 series airplanes). That action, 

published in the Federal Register on 

April 6, 2005 (70 FR 17340), proposed 

to require an inspection for evidence of 

chafing between the hydraulic flexible 

hose and the ram air turbine (RAT) hub, 

and related investigative and corrective 

actions if necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment that was 

submitted on the proposed AD. 

Request To Revise Compliance Time 

The commenter requests that the 

compliance time be revised from the 

proposed 2,500 flight hours after the 

effective date of the AD to 15 months 

after the effective date of the AD. 

However, the commenter acknowledges 

that the 2,500-flight-hour compliance 

time should be sufficient for the 12 U.S.-

registered airplanes to receive the 

required inspection. The commenter 

notes that revising the compliance time 

would allow the proposed inspection to 

be accomplished during a regularly 

scheduled C-check. The commenter 

notes that it has no affected airplanes in 

its fleet. The commenter also states that, 

based on its experience, replacing the 

RAT would take about 3 hours. 

We do not concur with the 

commenter’s request to revise the 

compliance time. In developing an 

appropriate compliance time for this 

AD, we considered the manufacturer’s 

recommendation; the recommendation 

of the Direction Ge ́ne ́rale de l’Aviation 

Civile, which is the airworthiness 

authority for France; the degree of 

urgency associated with the subject 

unsafe condition; the average utilization 

of the affected fleet; the maintenance 

schedules of the majority of affected 

operators; and the time necessary to 

perform the inspection (1 work hour). In 

light of all of these factors, we find that 

a 2,500-flight-hour compliance time 

represents an appropriate interval of