66870 Federal Register / Vol. 60, No. 248 / Wednesday, December 27, 1995 / Rules and Regulations

three conformed copies with exhibits,

and three conformed copies without

exhibits, to the Dissemination Branch,

Records Management and Information

Policy; and

(ii) Two copies, which shall include

one manually signed copy with exhibits

and one conformed copy, without

exhibits, to the Regional Director.

(2) Within five days after the effective

date of an offering circular or the

commencement of a public offering after

the effective date, whichever occurs

later, nine copies of the offering circular

used shall be filed with the OTS, as

follows: seven copies to the

Dissemination Branch, Records

Management and Information Policy,

and two copies to the Regional Director.

* * * * *

§ 563g.22 [Removed]

33. Section 563g.22 is removed.

PART 571—STATEMENTS OF POLICY

34. The authority citation for part 571

continues to read as follows:

Authority: 5 U.S.C. 552, 559; 12 U.S.C.

1462a, 1463, 1464.

§ 571.24 [Amended]

35. Section 571.24 is amended by

removing the phrase ‘‘parts 528 and

529’’ in paragraph (a), and by adding in

lieu thereof the phrase ‘‘part 528’’.

PART 583—DEFINITIONS

36. The authority citation for part 583

is revised to read as follows:

Authority: 12 U.S.C. 1462, 1462a, 1463,

1464, 1467a, 1468.

§ 583.17 [Amended]

37. Section 583.17 is amended by

removing the phrase ‘‘§ 584.6 of this

chapter’’, and by adding in lieu thereof

the phrase ‘‘12 U.S.C. 1467a(m)’’.

PART 584—REGULATED ACTIVITIES

38. The authority citation for part 584

continues to read as follows:

Authority: 12 U.S.C. 1462, 1462a, 1463,

1464, 1467a, 1468.

§ 584.2a [Amended]

39. Section 584.2a is amended by

removing the phrase ‘‘§ 584.6 of this

chapter’’ in paragraph (a)(2), and by

adding in lieu thereof the phrase ‘‘12

U.S.C. 1467a(m)’’.

§ 584.2–1 [Amended]

40. Section 584.2–1 is amended by

removing the phrase ‘‘§ 584.3 of this

part’’ where it appears in paragraphs

(b)(2) and (b)(3) introductory text, and

by adding in lieu thereof the phrase ‘‘12

U.S.C. 1468’’.

§§ 584.3, 584.6, 584.11 [Removed]

41. Sections 584.3, 584.6 and 584.11

are removed.

Dated: December 8, 1995.

By the Office of Thrift Supervision.

Jonathan L. Fiechter,

Acting Director.

[FR Doc. 95–31121 Filed 12–26–95; 8:45 am]

BILLING CODE 6720–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–NM–246–AD; Amendment

39–9469; AD 95–26–11]

Airworthiness Directives; Lockheed

Model L–1011–385 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to all Lockheed Model L–

1011–385 series airplanes, that currently

requires visual inspections to detect

cracking of the fittings that attach the aft

pressure bulkhead to the fuselage

stringers. That AD also currently

requires replacement of cracked fittings,

and repair of adjacent structure if found

to be cracked. This amendment requires

new repetitive inspections to detect

cracking of the fittings and of the splice

tab of the aft pressure bulkhead, and

corrective actions, if necessary. This

amendment is prompted by the results

of the visual inspections performed in

accordance with the existing AD, which

indicate that the visual inspection is

inadequate to detect fatigue cracking.

The actions specified in this AD are

intended to prevent fatigue cracking of

the aft pressure bulkhead, which could

lead to failure of the end fittings and

splice tabs, and subsequent rapid

decompression of the airplane during

flight.

DATES: Effective January 11, 1996.

The incorporation by reference of

certain publications listed in the

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), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 95–NM–

246–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

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, 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.

FOR FURTHER INFORMATION CONTACT:

Thomas Peters, Aerospace Engineer,

Systems and Flight Test Branch, ACE–

116A, FAA, Atlanta Aircraft

Certification Office, Small Airplane

Directorate, Campus Building, 1701

Columbia Avenue, Suite 2–160, College

Park, Georgia; telephone (404) 305–

7367; fax (404) 305–7348.

SUPPLEMENTARY INFORMATION: On

September 6, 1995, the FAA issued AD

95–18–52, amendment 39–9366 (60 FR

47465, September 13, 1995), which is

applicable to all Lockheed Model L–

1011–385 series airplanes. That AD

requires repetitive detailed visual

inspections to detect cracking of the

fittings that attach the aft pressure

bulkhead to the fuselage stringers at

stringers 1 through 10 and at stringers

64 through 56, and various follow-on

actions. That action was prompted by

reports of cracks found in these fittings.

The actions required by that AD are

intended to prevent fatigue cracking that

can lead to failure of the fittings that

attach the aft pressure bulkhead to the

fuselage stringer, and subsequent rapid

decompression of the airplane during

flight.

The FAA has reviewed the findings

from the visual inspections performed

in accordance with AD 95–18–52, and

from eddy current inspections

performed voluntarily by an operator.

The eddy current inspections revealed

findings of cracks in the end fittings;

these same fittings had been inspected

previously using the visual inspection

technique required by the existing AD

and this cracking was identified. In light

of these findings, the FAA has

determined that the currently required

visual inspections are inadequate to

detect all fatigue cracking. Such fatigue

cracking, if not detected and corrected

in a timely manner, could lead to failure

of the fittings and splice tabs of the aft

pressure bulkhead, and subsequently
Federal Register / Vol. 60, No. 248 / Wednesday, December 27, 1995 / Rules and Regulations 66871

could result in rapid decompression of

the airplane during flight.

The FAA has reviewed and approved

Lockheed L–1011 Service Bulletin 093–

53–105, Revision 1, dated November 17,

1995, which describes procedures for:

1. Repetitive eddy current surface

scan (ECSS) inspections to detect

cracking of the end fittings that attach

the aft pressure bulkhead to the fuselage

stringers at stringers 1 through 14 (right

side) and at stringers 52 through 64 (left

side);

2. Repetitive ECSS inspections to

detect cracking of the lower (or inner)

surface of the upper bonded splice tab

of the bulkhead assembly at stringers 1

through 14 and at stringers 52 through

64.

3. If any end fitting is found cracked,

replacement of a fitting with a new

fitting without pilot holes, rework of the

fitting, and various follow-on actions

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

borescope inspections; and repair) of the

inner and outer tee caps; and

4. A bolt hole eddy current inspection

to detect cracking of the forward flange

of the inner tee cap, if any fastener is

found cracked; and repair, if necessary.

Accomplishment of the ECSS

inspections described in this service

bulletin would eliminate the need for

the repetitive visual inspections.

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of this same

type design, this AD supersedes AD 95–

18–52 to continue to require repetitive

detailed visual inspections to detect

cracking of the fittings that attach the aft

pressure bulkhead to the fuselage

stringers at stringers 1 through 10 (right

side) and at stringers 56 through 64 (left

side). This AD adds a requirement to

conduct repetitive ECSS inspections to

detect cracking of the end fittings and of

the splice tab at stringers 1 through 14

(right side) and at stringers 52 through

64 (left side) of the aft pressure

bulkhead, and corrective actions, if

necessary.

Once the ECSS inspections are

initiated, the repetitive visual

inspection requirements of this AD are

terminated.

The previous requirement of AD 95–

18–52 to submit a report of inspection

findings to the FAA has been deleted

from this AD.

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 shall 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 rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 95–NM–246–AD.’’ 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 that it 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.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing amendment 39–9366 (60 FR

47465, September 13, 1995), and by

adding a new airworthiness directive

(AD), amendment 39–9469, to read as

follows:

95–26–11 Lockheed: Amendment 39–9469.

Docket 95–NM–246–AD. Supersedes AD

95–18–52, Amendment 39–9366.

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 use the authority

provided in paragraph (h) 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 of the aft

pressure bulkhead, which could lead to

failure of the end fittings and splice tab, and
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