2902 Federal Register / Vol. 61, No. 20 / Tuesday, January 30, 1996 / Rules and Regulations

The Board will review and act upon

each such request on a case-by-case

basis.

* * * * *

By order of the Board of Governors of the

Federal Reserve System, January 24, 1996.

William W. Wiles,

Secretary of the Board.

[FR Doc. 96–1650 Filed 1–29–96; 8:45 a.m.]

BILLING CODE 6210–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94–NM–178–AD; Amendment

39–9498; AD 95–13–11 R1]

Airworthiness Directives; McDonnell

Douglas Model DC–10–10 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; correction.

SUMMARY: This amendment clarifies

information in an existing airworthiness

directive (AD), applicable to certain

McDonnell Douglas Model DC–10–10

airplanes, that currently requires

repetitive inspections to detect cracking

of the upper caps in the front spar of the

left and right wing, and repair, if

necessary. The actions specified in that

AD are intended to prevent progression

of fatigue cracking, which could cause

reduced structural integrity of the wing

front spar and damage to adjacent

structures. This amendment clarifies the

requirements of the current AD by

revising the area of inspection. This

amendment is prompted by

communications received from affected

operators that the current requirements

of the AD are unclear.

DATES: Effective August 7, 1995.

The incorporation by reference of

certain publications listed in the

regulations was approved previously by

the Director of the Federal Register as

of August 7, 1995 (60 FR 35326, July 7,

1995).

ADDRESSES: The service information

referenced in this AD may be obtained

from McDonnell Douglas Corporation,

3855 Lakewood Boulevard, Long Beach,

California 90846, Attention: Technical

Publications Business Administration,

Department C1–L51 (2–60). 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, Los

Angeles Aircraft Certification Office,

Transport Airplane Directorate, 3960

Paramount Boulevard, Lakewood,

California; or at the Office of the Federal

Register, 800 North Capitol Street NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: John

Cecil, Aerospace Engineer, Airframe

Branch, ANM–120L, FAA, Transport

Airplane Directorate, Los Angeles

Aircraft Certification Office, 3960

Paramount Boulevard, Lakewood,

California 90712; telephone (310) 627–

5322; fax (310) 627–5210.

SUPPLEMENTARY INFORMATION: On June

22, 1995, the FAA issued AD 95–13–11,

amendment 39–9291 (60 FR 35326, July

7, 1995), which is applicable to certain

McDonnell Douglas Model DC–10–10

airplanes. That AD requires repetitive

eddy current test high frequency (ETHF)

surface inspections to detect fatigue

cracking, and repair of the upper cap in

the front spar of the wing if any cracking

is found. That AD also requires

additional repetitive inspections after

any repair of the upper cap.

Additionally, that AD stipulates that, if

the preventive modification is installed

on an airplane on which no cracks are

found during the initial inspection, the

repetitive inspections may be

terminated. That action was prompted

by reports of fatigue cracking in the

upper cap of the front spar of the wing

in the forward flange area. The actions

required by that AD are intended to

prevent progression of fatigue cracking,

which could cause reduced structural

integrity of the wing front spar and

damage to adjacent structures.

Since the issuance of that AD, the

FAA has received communications from

affected operators that the area defined

for the ETHF surface inspection is

unclear. Specifically, these operators

have indicated that the referenced

McDonnell Douglas DC–10 Service

Bulletin 57–129, dated August 12, 1994,

recommends inspection of the upper

cap of the front spar of the left and right

wing ‘‘between’’ stations Xos 667.678

and Xos 789.645 in certain paragraphs

but describes the inspection ‘‘at’’

stations Xos 667.678 and Xos 789.645 in

the accomplishment instructions. AD

95–13–11 requires inspection

‘‘between’’ stations Xos 667.678 and Xos

789.645.

These operators have therefore,

requested that the FAA clarify the AD

to indicate exactly what area is required

to be inspected.

In considering this request, and upon

further review of the wording of the

current AD, the FAA concurs that some

clarification is necessary.

It was the FAA’s intent that the

requirements of AD 95–13–11 be

parallel to those actions recommended

by the manufacturer in the

accomplishment instructions of its

referenced service bulletin. The

intended requirements of the AD were

that affected operators would conduct

the ETHF inspections to detect fatigue

cracks at the areas where cracking had

been reported, namely at stations Xos

667.678 and Xos 789.645. However, as

AD 95–13–11 is currently worded,

operators may incorrectly conduct

ETHF inspections ‘‘between’’ these

stations, rather than ‘‘at’’ those stations.

Such misunderstanding could result in

operators unnecessarily conducting

ETHF inspections at other stations,

which would be of no significant safety

value and would entail incurring

needless additional costs in labor and

downtime.

Operators should note that the

economic information supplied in the

preamble of AD 95–13–11 remains

unchanged since that information was

based on the workhours required to

perform the ETHF inspection at stations

Xos 667.678 and Xos 789.645, in

accordance with data supplied in

McDonnell Douglas Service Bulletin 57–

129, dated August 12, 1994.

Since it is obvious that the required

ETHF inspection area is not totally clear

in the way that AD 95–13–11 is

currently worded, the FAA has

determined that the wording of

paragraph (a) of the AD must be revised

to clarify the intent of the required

actions. This action revises that

paragraph to specify that the inspection

area is at stations Xos 667.678 and Xos

789.645.

Action is taken herein to clarify these

requirements of AD 95–13–11 and to

correctly add the AD as an amendment

to section 39.13 of the Federal Aviation

Regulations (14 CFR 39.13).

The final rule is being reprinted in its

entirety for the convenience of affected

operators. The effective date remains

August 7, 1995.

Since this action only clarifies a

current requirement, 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:
Federal Register / Vol. 61, No. 20 / Tuesday, January 30, 1996 / Rules and Regulations 2903

PART 39—AIRWORTHINESS

DIRECTIVES

1. The authority citation for part 39

continues to read as follows:

Authority: 49 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing amendment 39–9291 (60 FR

35326, July 7, 1995), and by adding a

new airworthiness directive (AD),

amendment 39–9498, to read as follows:

95–13–11 R1 McDonnell Douglas:

Amendment 39–9498. Docket 94–NM–

178–AD. Revises AD 95–13–11,

Amendment 39–9291.

Applicability: Model DC–10–10 airplanes,

as listed in McDonnell Douglas DC–10

Service Bulletin 57–129, dated August 12,

1994; 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 (e) 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 reduced structural integrity of

the wing front spar and damage to adjacent

structures due to fatigue cracking in the

upper cap of the front spar of the wing,

accomplish the following:

(a) Prior to the accumulation of 10,000 total

landings, or within 1,800 landings after the

effective date of this AD, whichever occurs

later, perform an initial eddy current test

high frequency (ETHF) surface inspection to

detect cracks in the upper cap of the front

spar of the left and right wing at stations Xos

667.678 and Xos 789.645, in accordance with

McDonnell Douglas DC–10 Service Bulletin

57–129, dated August 12, 1994. Repeat this

inspection thereafter at the intervals

specified in paragraph (b) or (c) of this AD,

as applicable.

(b) For airplanes on which no crack is

found: Repeat the inspection required by

paragraph (a) of this AD thereafter at

intervals not to exceed 10,000 landings, or

accomplish the crack preventative

modification in accordance with McDonnell

Douglas DC–10 Service Bulletin 57–129,

dated August 12, 1994. Accomplishment of

that preventative modification constitutes

terminating action for the requirements of

this paragraph.

(c) For airplanes on which any crack is

found that is identified as ‘‘Condition II’’ in

McDonnell Douglas DC–10 Service Bulletin

57–129, dated August 12, 1994: Accomplish

paragraphs (c)(1) and (c)(2) of this AD in

accordance with that service bulletin.

(1) Prior to further flight, perform the

permanent repair for cracks in accordance

with the service bulletin; and

(2) Within 12,500 landings after the

installation of the permanent repair specified

in paragraph (c)(1) of this AD, perform an

ETHF surface inspection for cracks, in

accordance with the service bulletin. Repeat

this inspection thereafter at intervals not to

exceed 7,000 landings.

(d) For airplanes on which any crack is

found that is identified as ‘‘Condition III’’ in

McDonnell Douglas DC–10 Service Bulletin

57–129, dated August 12, 1994: Prior to

further flight, repair the cracking in

accordance with a method approved by the

Manager, Los Angeles Aircraft Certification

Office (ACO), FAA, Transport Airplane

Directorate.

(e) 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, Los

Angeles ACO. Operators shall submit their

requests through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Los Angeles ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

(f) 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.

(g) The inspections, modification, and

permanent repair shall be done in accordance

with McDonnell Douglas DC–10 Service

Bulletin 57–129, dated August 12, 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 August 7, 1995 (60

FR 35326, July 7, 1995). Copies may be

obtained from McDonnell Douglas

Corporation, 3855 Lakewood Boulevard,

Long Beach, California 90846, Attention:

Technical Publications Business

Administration, Department C1–L51 (2–60).

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

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

FAA, Transport Airplane Directorate, Los

Angeles Aircraft Certification Office, 3960

Paramount Boulevard, Lakewood, California;

or at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

(g) This amendment is effective on August

7, 1995.

Issued in Renton, Washington, on January

22, 1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–1569 Filed 1–29–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 97

[Docket No. 28426; Amdt. No. 1703]

Standard Instrument Approach

Procedures; Miscellaneous

Amendments

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This amendment establishes,

amends, suspends, or revokes Standard

Instrument Approach Procedures

(SIAPs) for operations at certain

airports. These regulatory actions are

needed because of the adoption of new

or revised criteria, or because of changes

occurring in the National Airspace

System, such as the commissioning of

new navigational facilities, addition of

new obstacles, or changes in air traffic

requirements. These changes are

designed to provide safe and efficient

use of the navigable airspace and to

promote safe flight operations under

instrument flight rules at the affected

airports.

DATES: An effective date for each SIAP

is specified in the amendatory

provisions.

Incorporation by reference-approved

by the Director of the Federal Register

on December 31, 1980, and reapproved

as of January 1, 1982.

ADDRESSES: Availability of matters

incorporated by reference in the

amendment is as follows:

For Examination—

1. FAA Rules Docket, FAA

Headquarters Building, 800

Independence Avenue SW.,

Washington, DC 20591;

2. The FAA Regional Office of the

region in which the affected airport is

located; or

3. The Flight Inspection Area Office

which originated the SIAP.

For Purchase—Individual SIAP

copies may be obtained from:

1. FAA Public Inquiry Center (APA–

200), FAA Headquarters Building, 800

Independence Avenue SW.,

Washington, DC 20591; or

2. The FAA Regional Office of the

region in which the affected airport is

located.

By Subscription—Copies of all SIAPs,

mailed once every 2 weeks, are for sale