63414 Federal Register / Vol. 60, No. 237 / Monday, December 11, 1995 / Rules and Regulations

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Standardization

Branch, ANM–113.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(d) 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.

(e) This amendment becomes effective on

January 10, 1996.

Issued in Renton, Washington, on

December 5, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–30134 Filed 12–8–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 93–NM–219–AD; Amendment

39–9454; AD 95–20–04 R1]

Airworthiness Directives; Lockheed

Model L–1011–385–1 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; correction.

SUMMARY: This amendment revises an

existing airworthiness directive (AD),

applicable to all Lockheed Model L–

1011–385–1 series airplanes, that

currently requires implementation of a

Supplemental Inspection Document

(SID) program of structural inspections

to detect fatigue cracking, and repair, if

necessary, to ensure continued

airworthiness of these airplanes as they

approach the manufacturer’s original

fatigue design life goal. That AD

originally was prompted by a structural

re-evaluation by the manufacturer that

identified certain structural details

where fatigue damage is likely to occur.

The actions specified in that AD are

intended to prevent fatigue cracking that

could compromise the structural

integrity of these airplanes. This

amendment corrects the compliance

time for the initial inspection of each

structurally significant detail (SSD).

DATES: Effective November 2, 1995.

The incorporation by reference of

certain publications listed in the

regulations was approved previously by

the Director of the Federal Register as of

November 2, 1995 (60 FR 51713,

October 3, 1995).

ADDRESSES: The service information

referenced in this AD may be obtained

from Lockheed Aeronautical Systems

Support Company, Field Support

Department, Dept. 693, Zone 0755, 2251

Lake Park Drive, Smyrna, Georgia

30080. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at

the FAA, Small Airplane Directorate,

Atlanta Aircraft Certification Office,

Campus Building, 1701 Columbia

Avenue, Suite 2–160, College Park,

Georgia; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Thomas Peters, Aerospace Engineer,

Flight Test Branch, ACE–116A, FAA,

Small Airplane Directorate, Atlanta

Aircraft Certification Office, Campus

Building, 1701 Columbia Avenue, Suite

2–160, College Park, Georgia 30337–

2748; telephone (404) 305–7367; fax

(404) 305–7348.

SUPPLEMENTARY INFORMATION: On

September 20, 1995, the FAA issued AD

95–20–04, amendment 39–9382 (60 FR

51713, October 3, 1995), applicable to

all Lockheed Model L–1011–385–1

series airplanes. That AD requires

implementation of a Supplemental

Inspection Document (SID) program of

structural inspections to detect fatigue

cracking, and repair, if necessary, to

ensure continued airworthiness of these

airplanes as they approach the

manufacturer’s original fatigue design

life goal. That action was prompted by

a structural re-evaluation by the

manufacturer that identified certain

structural details where fatigue damage

is likely to occur. The actions required

by that AD are intended to prevent

fatigue cracking that could compromise

the structural integrity of these

airplanes.

Since the issuance of that AD, the

FAA has received communications from

an affected operator indicating

confusion about the compliance time for

accomplishing the inspections of each

structurally significant detail (SSD).

This operator points out that the AD

specifies, first, that the inspections

contained in the SID must be

incorporated into the FAA-approved

maintenance program within 12 months

after the effective date of the AD.

Second, the AD requires that the initial

inspection of each SSD must be

accomplished within one repeat interval

after the effective date of the AD. The

operator points out that this presents a

problem in complying with the AD,

since, in some cases, the initial

inspection of an SSD may be required to

be accomplished prior to the

incorporation of the SID program into

an operator’s maintenance program.

The FAA has reviewed the

compliance time specified in AD 95–

20–04, and finds that it is indeed

erroneous. It was the FAA’s intent that

the SID program be incorporated into

the FAA-approved maintenance

inspection program prior to the

performance of any inspection

contained in the SID. Therefore, the

FAA has determined that it is

appropriate to take action to correct

paragraph (a)(1) of that AD to specify

that the compliance time for performing

the initial inspection of each SSD is

within one repeat interval measured

from a date 12 months after November

2, 1995 (the effective date of the AD).

The FAA finds that this change will not

compromise safety and is consistent

with what the FAA had originally

intended.

Action is taken herein to correct the

error and to correctly add the AD as an

amendment to section 39.13 of the

Federal Aviation Regulations (14 CFR

39.13). The effective date of the rule

remains November 2, 1995.

The final rule is being reprinted in its

entirety for the convenience of affected

operators.

Since this AD merely corrects the

compliance time for a previouslyrequired action, it requires no additional

work to be performed by affected

operators. In light of this, the FAA has

determined that it has no adverse

economic impact and imposes no

additional burden on any person.

Therefore, notice and public procedures

hereon are unnecessary.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Correction

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 USC 106(g), 40101, 40113,

44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing amendment 39–9382 (60 FR

51713, October 3, 1995), and by adding
Federal Register / Vol. 60, No. 237 / Monday, December 11, 1995 / Rules and Regulations 63415

a new airworthiness directive (AD),

amendment 39– , to read as follows:

95–20–04 R1 Lockheed: Amendment 39–

9454. Docket 93–NM–219–AD. Revises

AD 95–20–04, Amendment 39–9382.

Applicability: Model L–1011–385–1, L–

1011–385–1–14, and L–1011–385–1–15

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 use the authority

provided in paragraph (d) of this AD to

request approval from the FAA. This

approval may address either no action, if the

current configuration eliminates the unsafe

condition; or different actions necessary to

address the unsafe condition described in

this AD. Such a request should include an

assessment of the effect of the changed

configuration on the unsafe condition

addressed by this AD. In no case does the

presence of any modification, alteration, or

repair remove any airplane from the

applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent fatigue cracking that could

compromise the structural integrity of these

airplanes, accomplish the following:

(a) Within 12 months the effective date of

this AD, incorporate a revision into the FAAapproved maintenance inspection program

which provides for inspection(s) of the

structurally significant details (SSD) defined

in Lockheed Document Number

LG92ER0060, ‘‘L–1011–385 Series

Supplemental Inspection Document,’’ revised

January 1994.

(1) The initial inspection for each SSD

must be performed at the later of the times

specified in paragraph (a)(1)(i) or (a)(1)(ii) of

this AD:

(i) Within one repeat interval measured

from a date 12 months after the effective date

of this AD; or

(ii) Prior to the threshold specified in the

Lockheed Document for that SSD.

(2) A 10 percent deviation from the

repetitive interval specified in the Lockheed

Document for that SSD is acceptable to allow

for planning and scheduling time.

(3) If the Lockheed Document specifies that

inspection of any SSD be performed at every

‘‘C’’ check, those inspections must be

performed at intervals not to exceed 5,000

hours time-in-service or 2,500 flight cycles,

whichever occurs earlier.

(4) If the Lockheed Document specifies

either the initial inspection or the repetitive

inspection intervals for any SSD in terms of

flight hours or flight cycles, the inspection

shall be performed prior to the earlier of the

terms (whichever occurs first on the airplane:

either accumulated number of flight hours, or

accumulated number of flight cycles).

(5) The non-destructive inspection

techniques referenced in Appendix VI of the

Lockheed Document provide acceptable

methods for accomplishing the inspections

required by this AD.

(b) If any cracking is found in any SSD,

prior to further flight, repair in accordance

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

AD.

(1) In accordance with the applicable

service bulletin referenced in Lockheed

Document Number LG92ER0060, ‘‘L–1011–

385 Series Supplemental Inspection

Document,’’ revised January 1994; or

(2) In accordance with the Structural

Repair Manual; or

(3) In accordance with a method approved

by the Manager, Atlanta Aircraft Certification

Office (ACO), FAA, Small Airplane

Directorate.

(c) Within 30 days after returning the

airplane to service, subsequent to

accomplishment of the inspection(s)

specified in Lockheed Document Number

LG92ER0060, ‘‘L–1011–385 Series

Supplemental Inspection Document,’’ revised

January 1994, submit a report of the results

(positive or negative) of the inspection(s) to

Lockheed in accordance with Section V.,

Data Reporting System (DRS), of the

Lockheed Document. Information collection

requirements contained in this regulation

have been approved by the Office of

Management and Budget (OMB) under the

provisions of the Paperwork Reduction Act of

1980 (44 U.S.C. 3501 et seq.) and have been

assigned OMB Control Number 2120–0056.

(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, Small Airplane Directorate.

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.

(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.

(f) The incorporation of the revision and

reporting requirements shall be done in

accordance with Lockheed Document

Number LG92ER0060, ‘‘L–1011–385 Series

Supplemental Inspection Document,’’ revised

January 1994. This incorporation by

reference was approved previously by the

Director of the Federal Register in accordance

with 5 U.S.C. 552(a) and 1 CFR part 51 as of

November 2, 1995 (60 FR 51713, October 3,

1995). Copies may be obtained from

Lockheed Aeronautical Systems Support

Company, Field Support Department, Dept.

693, Zone 0755, 2251 Lake Park Drive,

Smyrna, Georgia 30080. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Atlanta Aircraft

Certification Office, Small Airplane

Directorate, Campus Building, 1701

Columbia Avenue, Suite 2–160, College Park,

Georgia; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

(g) This amendment is effective on

November 2, 1995.

Issued in Renton, Washington, on

December 5, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–30132 Filed 12–8–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 71

[Airspace Docket No. 95–ACE–09]

Amendment to Class E Airspace;

Council Bluffs, IA

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This amendment modifies the

Class E airspace area at Council Bluffs,

IA to accommodate a Global Positioning

System (GPS) Standard Instrument

Approach Procedure (SIAP) at the

Council Bluffs Municipal Airport. This

action will provide for additional

controlled airspace necessary for the

GPS SIAP.

EFFECTIVE DATE: 0901 UTC, April 25,

1996.

FOR FURTHER INFORMATION CONTACT:

Kathy Randolph, Air Traffic Operations

Branch, ACE–530C, Federal Aviation

Administration, 601 E. 12th St., Kansas

City, MO 64106; telephone (816) 426–

3408.

SUPPLEMENTARY INFORMATION:

History

On October 3, 1995, the FAA

proposed to amend part 71 of the

Federal Aviation Regulations (14 CFR

part 71) by modifying the Class E

airspace area at Council Bluffs, IA (60

FR 51747). The proposed action would

provide additional controlled airspace

to accommodate a GPS SIAP to runway

31 at the Council Bluffs Municipal

Airport.

Interested parties were invited to

participate in this rulemaking

proceeding by submitting written

comments on the proposal to the FAA.

No comments objecting to the proposal

were received. Class E airspace areas

extending from 700 feet or more above

the surface of the earth are published in

paragraph 6005 of FAA order 7400.9C,

dated August 17, 1995, and effective

September 16, 1995, which is

incorporated by reference in 14 CFR

71.1. The Class E airspace designation

listed in this document will be

published subsequently in the Order.

The Rule

This amendment to part 71 of the

Federal Aviation Regulations (14 CFR