66872 Federal Register / Vol. 60, No. 248 / Wednesday, December 27, 1995 / Rules and Regulations

subsequent rapid decompression of the

airplane during flight, accomplish the

following:

Restatement of Actions Required by AD 95–

18–52, Amendment 39–9366

Perform a detailed visual inspection to

detect cracking of the fittings that attach the

aft pressure bulkhead to the fuselage stringers

(hereinafter referred to as ‘‘fittings’’) at

stringers 1 through 10 (right side) and at

stringers 56 through 64 (left side), at the later

of the times specified in either paragraph

(a)(1) or (a)(2) of this AD.

(1) Prior to the accumulation of 20,000

total flight cycles; or

(2) Within the next 25 flight cycles or 10

days after September 28, 1995 (the effective

date of AD 95–18–52, amendment 39–9366),

whichever occurs earlier.

(b) If any cracking is detected in the fitting

at either stringer 10 or stringer 56 during the

inspection required by paragraph (a) of this

AD, prior to further flight, perform a detailed

visual inspection to detect cracking of the

next adjacent fitting (i.e., at stringer 11 or 55).

If cracking is detected in that fitting, prior to

further flight, perform a detailed visual

inspection to detect cracking of the next

adjacent fitting (i.e., at stringer 12 or 54). If

cracking is detected in that fitting, prior to

further flight, continue to perform detailed

visual inspections to detect cracking of the

next adjacent fitting(s) until such a fitting is

found to be free of cracks.

(c) If any cracked fitting is detected during

the inspections required by either paragraph

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

accomplish the requirements of paragraphs

(c)(1) and (c)(2) of this AD.

(1) Replace the cracked fitting with a new

fitting, or with a serviceable fitting on which

a detailed visual inspection has been

performed previously to detect cracking and

that has been found to be free of cracks; and

(2) Perform a detailed visual inspection to

detect cracking in the radius at the lower end

of the vertical leg of the bulkhead T-shaped

frame between the stringer locations on

either side of the stringer having the cracked

fitting. If any cracked T-shaped frame is

detected, prior to further flight, repair in

accordance with a method approved by the

Manager, Atlanta Aircraft Certification Office

(ACO), FAA, Small Airplane Directorate.

(d) Repeat the inspections and other

necessary actions required by paragraphs (a),

(b), and (c) of this AD at intervals not to

exceed 1,800 flight cycles or 3,000 flight

hours, whichever occurs earlier, until

paragraph (e) of this AD is accomplished.

New Actions Required by This Amendment

(e) Except as provided by paragraph (f) of

this AD, prior to the accumulation of 20,000

flight cycles, or within 30 days after the

effective date of this AD, whichever occurs

later, accomplish the requirements of both

paragraphs (e)(1) and (e)(2) of this AD, in

accordance with Lockheed L–1011 Service

Bulletin 093–53–105, Revision 1, dated

November 17, 1995. Repeat the ECSS

inspections thereafter at intervals not to

exceed 2,500 flight cycles. Accomplishment

of the eddy current surface scan (ECSS)

inspection constitutes terminating action for

the repetitive inspection requirements of

paragraph (d) of this AD.

(1) Perform an ECSS inspection to detect

cracking of the fittings at stringers 1 through

14 (right side) and at stringers 52 through 64

(left side), in accordance with the service

bulletin. Except as provided by paragraph (g)

of this AD, if any cracking is detected, prior

to further flight, replace the fitting with a

new fitting without pilot holes, rework the

fitting, and perform various follow-on actions

(i.e., bolt hole eddy current, ECSS, and

borescope inspections; and repair) of the

inner and outer tee caps, in accordance with

the service bulletin. And

(2) Perform an ECSS inspection to detect

cracking of the lower (or inner) surface of the

upper bonded splice tab of the bulkhead

assembly at stringers 1 through 14 (right side)

and at stringers 52 through 64 (left side), in

accordance with the service bulletin.

(i) Except as provided by paragraph (g) of

this AD, if any cracking is detected at the

upper bonded splice tab, repair in

accordance with a method approved by the

Manager, Atlanta ACO, FAA, Small Airplane

Directorate.

(ii) Except as provided by paragraph (g) of

this AD, if any cracking is detected at a

fastener, prior to further flight, perform a bolt

hole eddy current (BHEC) inspection to

detect cracking of the forward flange of the

inner tee cap, in accordance with the service

bulletin. If any cracking is detected, prior to

further flight, repair in accordance with the

service bulletin.

(f) Accomplishment of the initial ECSS

inspections required by paragraph (e) of this

AD may be deferred to a date within 120 days

after the effective date of this AD provided

that, in the interim, a visual inspection as

specified in paragraph (a) of this AD is

accomplished within 30 days after the

effective date of this AD and repeated

thereafter at intervals not to exceed 50 flight

cycles. Once the ECSS inspections begin, the

visual inspections may be terminated.

(g) If two or more adjacent fittings on both

sides of the cracked fittings or bonded splice

tabs/fasteners are determined to be free of

cracks by the ECSS inspection required by

paragraph (e)(1) and (e)(2) of this AD, repeat

the ECSS inspection of the adjacent fittings

thereafter at intervals not to exceed 600 flight

cycles until the cracked fittings or splice

tabs/fasteners are replaced or repaired.

Within 2,500 total flight cycles after finding

the crack, replace or repair the cracked fitting

and/or splice tab/fasteners in accordance

with Lockheed L–1011 Service Bulletin 093–

53–105, Revision 1, dated November 17,

1995.

(h) 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. 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.

(i) 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.

(j) The actions shall be done in accordance

with Lockheed L–1011 Service Bulletin 093–

53–105, Revision 1, dated November 17,

1995. 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 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.

(k) This amendment becomes effective on

January 11, 1996.

Issued in Renton, Washington, on

December 18, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–31297 Filed 12–26–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–ANE–58; Amendment 39–

9461; AD 95–26–03]

Airworthiness Directives; Pratt and

Whitney JT8D Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to Pratt & Whitney (PW) JT8D

series turbofan engines, that currently

requires inspection, and replacement, if

necessary, of suspect 7th through 12th

stage high pressure compressor (HPC)

disks. This amendment adds 46 more

applicable engines, revises the

inspection requirements, incorporates a

new PW Alert Service Bulletin (ASB),

and requires reporting the results of the

inspection to the manufacturer. This

amendment is prompted by the

identification of additional suspect

engines, by the development of revised

inspection intervals, and by the

issuance of the new PW ASB. The

actions specified by this AD are

intended to prevent an uncontained

HPC disk failure, which can result in

damage to the aircraft.

DATES: Effective January 11, 1996.

The incorporation by reference of

certain publications listed in the
Federal Register / Vol. 60, No. 248 / Wednesday, December 27, 1995 / Rules and Regulations 66873

regulations is approved by the Director

of the Federal Register as of January 11,

1996.

Comments for inclusion in the Rules

Docket must be received on or before

February 26, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

95–ANE–58, 12 New England Executive

Park, Burlington, MA 01803–5299.

The service information referenced in

this AD may be obtained from Pratt &

Whitney, Publications Department, M/S

132–30, 400 Main St., East Hartford, CT

06108. This information may be

examined at the FAA, New England

Region, Office of the Assistant Chief

Counsel, Burlington, MA; or at the

Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Mark A. Rumizen, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (617) 238–7137,

fax (617) 238–7199.

SUPPLEMENTARY INFORMATION: On August

15, 1995, the Federal Aviation

Administration (FAA) issued

airworthiness directive (AD) 95–15–51,

Amendment 39–9345 (60 FR 43963,

August 24, 1995), applicable to Pratt &

Whitney (PW) JT8D series engines with

specified serial numbers, to require

inspection, and replacement if

necessary, of suspect 7th through 12th

stage high pressure compressor (HPC)

disks. That action was prompted by a

report that on June 8, 1995, a PW JT8D–

9A engine, installed on a McDonnell

Douglas DC–9–32 aircraft, experienced

an uncontained engine failure during

takeoff at the William B. Hartsfield

International Airport in Atlanta,

Georgia. The FAA determined that the

7th stage HPC disk failed due to a

fatigue crack that originated at a

corrosion pit in a shielding hole. The

FAA further determined that the fatigue

crack origination could have resulted

from a disk inspection not performed in

accordance with all practices and

procedures specified by the FAA and

PW. This disk inspection was performed

at Turk Hava Yollari (THY), a Turkish

engine overhaul and maintenance

facility. The FAA identified 24 suspect

engines in that AD that had been

overhauled by THY for which HPC disk

inspection was required. That

condition, if not corrected, could result

in an uncontained HPC disk failure,

which can result in damage to the

aircraft.

Since the issuance of that AD, the

FAA has identified an additional 46

suspect engines, based on a review of

records from the THY facility. In

addition, the FAA has also developed

revised inspection intervals, based on

further examination and analysis of

suspect disks. Also, PW has issued Alert

Service Bulletin (ASB) No. A6226, dated

October 17, 1995. Finally, this

superseding AD requires reporting the

results of the inspection to the

manufacturer. The FAA has reviewed

and approved the technical contents of

that ASB, which defines inspection

requirements of these suspect disks.

Since an unsafe condition has been

identified that is likely to exist or

develop on other engines of this same

type design, this AD supersedes AD 95–

15–51 to add 46 more applicable

engines, to revise the inspection

requirements, to incorporate PW ASB

No. A6226, dated October 17, 1995, and

to report the results of the inspection to

the manufacturer. The actions are

required to be accomplished in

accordance with the ASB described

previously.

Since a situation exists that requires

the immediate adoption of this

regulation, it is found 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

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this rule by

submitting such written data, views, or

arguments as they may desire.

Communications should identify the

Rules Docket number and be submitted

in triplicate to the address specified

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 95–ANE–58.’’ The

postcard will be date stamped and

returned to the commenter.

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and is not a ‘‘significant regulatory

action’’ under Executive Order 12866. It

has been determined further that this

action involves an emergency regulation

under DOT Regulatory Policies and

Procedures (44 FR 11034, February 26,

1979). If it is determined that this

emergency regulation otherwise would

be significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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 USC 106(g), 40101, 40113,

44701.
66874 Federal Register / Vol. 60, No. 248 / Wednesday, December 27, 1995 / Rules and Regulations

§ 39.13 [AMENDED]

2. Section 39.13 is amended by

removing Amendment 39—9345 (60 FR

43963, August 24, 1995), and by adding

a new airworthiness directive,

Amendment 39–9461, to read as

follows:

95–26–03 Pratt & Whitney: Amendment 39–

9461. Docket 95–ANE–58. Supersedes

AD 95–15–51, Amendment 39–9345.

Applicability: Pratt & Whitney (PW)

Models JT8D–1, –1A, –1B, –7, –7A, –9, –9A,

–11, –15, –15A, –17, –17A, –17R, –17AR

engines with serial numbers specified in

Section 2 of PW Alert Service Bulletin (ASB)

No. A6226, dated October 17, 1995. These

engines are installed on but not limited to

Boeing B727 and B737, and McDonnell

Douglas DC–9 aircraft.

Note: This airworthiness directive (AD)

applies to each engine 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 engines 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 (c)

to request approval from the Federal Aviation

Administration (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 engine from the

applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent an uncontained high pressure

compressor (HPC) disk failure, which can

result in damage to the aircraft, accomplish

the following:

(a) Perform a records search, inspect if

necessary, repair or replace if necessary, and

report results, of stage 7 through 12 HPC

disks in accordance with the intervals and

procedures of paragraph 2.A through 2.D of

PW ASB No. A6226, dated October 17, 1995.

Reporting requirements have been approved

by the Office of Management and Budget and

assigned OMB control number 2120–0056.

(b) For the purpose of this AD, the

accomplishment effective date to be used for

determination of inspection intervals, as

required by Section 2.B of PW ASB A6226,

dated October 17, 1995, is defined as the

effective date of this AD.

(c) 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, Engine

Certification Office. The request should be

forwarded through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

Note: Information concerning the existence

of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

(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 aircraft to

a location where the requirements of this AD

can be accomplished.

(e) The actions required by this AD shall

be done in accordance with the following

service document:

Document No. Pages Revision Date

PW ASB No. A6226 .................................................................................................................................. 1–20 Original .. October 17, 1995.

Total pages: 20.

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 Pratt & Whitney, Publications

Department, M/S 132–30, 400 Main St., East

Hartford, CT 06108. Copies may be inspected

at the FAA, New England Region, Office of

the Assistant Chief Counsel, 12 New England

Executive Park, Burlington, MA; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(f) This amendment becomes effective on

January 11, 1996.

Issued in Burlington, Massachusetts, on

December 11, 1995.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 95–31332 Filed 12–26–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 91

[Docket No. 24456; Amendment No. 91–247]

Special VFR Weather Minimums

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule; technical

amendment.

SUMMARY: This action corrects the

Special visual flight rules (SVFR)

weather minimums in Alaska.

Specifically, this action allow SVFR

operations in Alaska when the sun is 6

degrees or more below the horizon.

EFFECTIVE DATE: December 27, 1995.

FOR FURTHER INFORMATION CONTACT:

Janet Apple, Air Traffic Rules Branch,

ATP–230, Airspace Rules and

Aeronautical Information Division,

Federal Aviation Administration, 800

Independence Avenue, SW.,

Washington, DC 20591; telephone (202)

267–8783.

SUPPLEMENTARY INFORMATION: On

December 17, 1991, the FAA published

the Airspace Reclassification final rule

(56 FR 65638) that, in pertinent part,

changed regulations and procedures in

regard to airspace classifications. These

changes, effective September 16, 1992,

were intended to simplify airspace

classifications to reduce airspace

complexity and thereby enhance safety.

Prior to the Airspace Reclassification

final rule, § 91.157 of Title 14, Code of

Federal Regulations (14 CFR) stated that

no person may operate an aircraft (other

than a helicopter) in a control zone

under the special weather minimums of

section 91.157 between sunset and

sunrise (or in Alaska, when the sun is

more than 6 degrees below the horizon),

with additional conditions. However,

the amendment language in the

Airspace Reclassification final rule

(Amdt. 91–227 56 FR 65660, December

17, 1991) inadvertently changed section

91.157 to read ‘‘* * * 6 degrees or

more above the horizon.’’ This technical

amendment corrects that error.

The Amendment

This amendment to 14 CFR part 91

subparagraph (b)(4) revises the

restriction for Special VFR operations in

Alaska to 6 degrees or more below the

horizon. The FAA has determined that

this action: (1) Is not a ‘‘major rule’’

under Executive Order 12291; (2) is not

a ‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034; February 26, 1979); and (3)

does not warrant preparation of a

regulatory evaluation as the anticipated

impact is negligible.

This action is a clarification of an

existing rule and does not place any

new restrictions or requirements on the

public, but rather lifts certain

restrictions presently in place. Notice

and public procedure under 5 U.S.C.

553(b) are unnecessary.

List of Subjects in 14 CFR Part 91

Air traffic control, Aircraft, Airmen,

Airports, Aviation safety.