3550 Federal Register / Vol. 61, No. 22 / Thursday, February 1, 1996 / Rules and Regulations

PART 105—DOCUMENT FILING (2

U.S.C. 432(g))

9. The authority citation for Part 105

continues to read as follows:

Authority: 2 U.S.C. 432(g), 438(a)(8).

10. Section 105.1 is revised to read as

follows:

§ 105.1 Place of filing; House candidates

and their authorized committees (2 U.S.C.

432(g)(1)).

All designations, statements, reports,

and notices, as well as any

modification(s) or amendment(s)

thereto, required to be filed under 11

CFR parts 101, 102, and 104 by a

candidate for nomination or election to

the office of Representative in, or

Delegate or Resident Commissioner to,

the Congress, or by his or her authorized

committee(s), shall be filed in original

form with, and received by, the Federal

Election Commission.

§ 105.4 [Amended]

11. Section 105.4 is amended by

removing ‘‘105.1,’’ and by removing the

comma after ‘‘105.2’’.

12. Section 105.5 is revised to read as

follows:

§ 105.5 Transmittal of microfilm copies

and photocopies of original reports filed

with the Secretary of the Senate to the

Commission (2 U.S.C. 432(g)(3)).

(a) Either a microfilmed copy or

photocopy of all original designations,

statements, reports, modifications or

amendments required to be filed

pursuant to 11 CFR 105.2 shall be

transmitted by the Secretary of the

Senate to the Commission as soon as

possible, but in any case no later than

two (2) working days after receiving

such designations, statements, reports,

modifications, or amendments.

(b) The Secretary of the Senate shall

then forward to the Commission a

microfilm copy and a photocopy of each

designation, statement, and report, or

any modification or amendment thereto,

filed with the Secretary pursuant to 11

CFR 105.2.

(c) The Secretary of the Senate shall

place a time and date stamp on each

original designation, statement, report,

modification or amendment received.

PART 109—INDEPENDENT

EXPENDITURES (2 U.S.C. 431(17),

434(c))

13. The authority citation for Part 109

continues to read as follows:

Authority: 2 U.S.C. 431(17), 434(c),

438(a)(8), 441d.

§ 109.2(a) [Amended]

14. Section 109.2(a) is amended by

removing ‘‘, the Clerk of the House’’.

PART 110—CONTRIBUTION AND

EXPENDITURE LIMITATIONS AND

PROHIBITIONS

15. The authority citation for Part 110

continues to read as follows:

Authority: 2 U.S.C. 431(8), 431(9),

432(c)(2), 437d(a)(8), 438(a)(8), 441a, 441b,

441d, 441e, 441f, 441g and 441h.

§ 110.6(c)(1) (i) and (ii) [Amended]

16. Section 110.6 is amended by

removing ‘‘, the Clerk of the House of

Representatives,’’ from paragraph

(c)(1)(i) and by removing ‘‘, Clerk’’ from

paragraph (c)(1)(ii).

PART 114—CORPORATE AND LABOR

ORGANIZATION ACTIVITY

17. The authority citation for Part 114

continues to read as follows:

Authority: 2 U.S.C. 431(8)(B), 431(9)(B),

432, 437d(a)(8),438(a)(8), and 441b.

§ 114.6(d)(3)(i) and (d)(5) [Amended]

18. Section 114.6 is amended by

removing ‘‘, the Clerk of the House’’

from paragraph (d)(3)(i) and by

removing ‘‘, the Clerk of the House,’’

from paragraph (d)(5).

Dated:January 26, 1996.

Lee Ann Elliott,

Chairman, Federal Election Commission.

[FR Doc. 96–1972 Filed 1–31–96; 8:45 am]

BILLING CODE 6715–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–NM–276–AD; Amendment

39–9496; AD 96–03–01]

Airworthiness Directives; Boeing

Model 747 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Boeing Model 747

series airplanes. This action requires

inspections of the lower engine mount

to determine if the tangential link upper

bolt and nut are oriented properly, and

if the tangential link upper bolt nut is

torqued within certain limits. This

action also requires replacement of the

bolt and nut with serviceable parts, if

necessary, and requires certain followon actions for airplanes on which the

upper bolt is missing. Terminating

action is also provided by this AD. This

amendment is prompted by reports of

migration of bolts completely from the

tangential link of the aft engine mount,

a condition which would reduce the

capability of the retention system for the

engine. The actions specified in this AD

are intended to prevent separation of the

engine from the airplane due to

migration of the tangential link upper

bolt.

DATES: Effective February 16, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February

16, 1996.

Comments for inclusion in the Rules

Docket must be received on or before

April 1, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 95–NM–

276–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from Boeing

Commercial Airplane Group, P.O. Box

3707, Seattle, Washington 98124–2207.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Tammy L. Dow, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue SW., Renton,

Washington; telephone (206) 227–2771;

fax (206) 227–1181.

SUPPLEMENTARY INFORMATION: Recently,

the FAA received reports indicating that

the upper bolt and nut of the tangential

link of the aft engine on Model 747

airplanes were found to have migrated

out of proper position. In three cases,

the bolt had completely backed out of

the hole. Analysis conducted by the

manufacturer demonstrated that the

nuts used to secure the bolts may not

provide adequate run-on torque.

Additionally, there was evidence that

lubricants were used on the threads of

some of the bolts. These conditions can

allow the nut to rotate and disengage

from the bolt. With no nut or other

retention for the bolt, normal vibration

causes the bolt to loosen and migrate

out of the tangential link. Loss of the

bolt would reduce the capability of the

engine retention system, and could

result in cracking of the engine turbine

exhaust case due to the increased load.

This condition, if not corrected, could
Federal Register / Vol. 61, No. 22 / Thursday, February 1, 1996 / Rules and Regulations 3551

result in separation of the engine from

the airplane.

The FAA has reviewed and approved

Boeing Alert Service Bulletin 747–

71A2277, dated November 29, 1995,

which describes procedures for

repetitive inspections of the lower

engine mount to verify if the tangential

link upper bolt nut is properly oriented

and to verify that the tangential link

upper bolt nut is torqued within certain

limits. Additionally, the service bulletin

describes procedures for the

replacement of the bolt and nut with

serviceable parts, if necessary. The alert

service bulletin also describes certain

other follow-on procedures for airplanes

on which the tangential link upper bolt

is missing. Those procedures involve a

visual inspection to detect damage and

deformation of the lower engine mount

lugs that attach the affected safety link;

magnetic particle inspections to detect

cracking of the lower engine mount

lugs; detail visual inspections to detect

cracking, bulging, discoloration, and

corrosion of the engine mounts and

adjacent structures; and replacement of

the lower engine mount fittings with

serviceable parts, if necessary;

installation of new safety links, bolts,

and nuts; and installation of the

tangential link upper bolt.

The FAA also has reviewed and

approved Boeing Service Bulletin 747–

71–2206, Revision 1, dated November

12, 1987 (as revised by Boeing 747

Notice of Status Change No. 747–71–

2206 NSC 1, dated December 4, 1987,

and Boeing 747 Notice of Status Change

No. 747–71–2206 NSC 2, dated March

17, 1988). This service information

describes procedures for replacement of

the safety links with modified safety

links. Accomplishment of this

replacement eliminates the need for

repetitive inspections of lower engine

mount bolt and nut.

Since an unsafe condition has been

identified that is likely to exist or

develop on other Boeing Model 747

series airplanes of the same type design,

this AD is being issued to prevent

possible separation of the engine from

the airplane due to consequences

associated with the complete migration

of the tangential link upper bolt. This

action requires repetitive visual

inspections to verify if the tangential

link upper bolt is correctly oriented;

inspections to determine if the

tangential link upper bolt nut is torqued

within certain limits; and replacement

of the bolt and nut with serviceable

parts, if necessary. This action also

requires certain other follow-on

procedures for airplanes on which the

tangential link upper bolt is missing.

Additionally, this AD provides for

replacement of the safety links as

optional terminating action for the

repetitive inspection requirements. The

actions are required to be accomplished

in accordance with the service bulletins

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.

This is considered to be interim

action. Once final action is identified,

the FAA may consider further

rulemaking.

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–276–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), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

96–03–01 Boeing: Amendment 39–9496.

Docket 95–NM–276–AD.

Applicability: Model 747 series airplanes,

as listed in Boeing Alert Service Bulletin

747–71A2277, dated November 29, 1995;

certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 (c) of this AD to

request approval from the FAA. This

approval may address either no action, if the
3552 Federal Register / Vol. 61, No. 22 / Thursday, February 1, 1996 / Rules and Regulations

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 separation of the engine from

the airplane, accomplish the following:

(a) Within 90 days after the effective date

of this AD, accomplish the requirements of

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

accordance with Boeing Alert Service

Bulletin 747–71A2277, dated November 29,

1995.

(1) Perform a visual inspection to ensure

that installation of the tangential link upper

bolt nut is on the forward side of the engine

mount fitting.

(i) If the tangential link upper bolt nut is

installed on the forward side of the engine

mount fitting, repeat the visual inspection at

intervals not to exceed 18 months.

(ii) If the tangential link upper bolt is not

installed on the forward side of the engine

mount fitting, prior to further flight, remove

the nut, bolt, and washers and reinstall the

nut, bolt, and washers in accordance with the

alert service bulletin. Thereafter, repeat the

visual inspection at intervals not to exceed

18 months.

(iii) If the tangential link upper bolt is

missing from the engine mount fitting, prior

to further flight, perform the various followon actions in accordance with the alert

service bulletin. (The follow-on actions

include visual inspections, magnetic particle

inspections, replacement of the lower engine

mount fitting with a serviceable part, if

necessary; installation of new safety links,

bolts, and nuts; and installation of a new

tangential link upper bolt.) Thereafter, repeat

the visual inspection at intervals not to

exceed 18 months.

(2) Perform an inspection to verify that the

torque value of the tangential link upper bolt

(on both sides of the mount) is within the

limits specified in the alert service bulletin.

(i) If the torque value of the tangential link

upper bolt nut is within the limits specified

in the alert service bulletin, repeat the

inspection (verification) at intervals not to

exceed 18 months.

(ii) If the torque value of the tangential link

upper bolt nut is outside the limits specified

in the alert service bulletin, prior to further

flight, perform a visual inspection of the

tangential link upper bolt and washer for any

damage or discrepancy, in accordance with

the alert service bulletin.

(A) If no damage or discrepancy of the

tangential link upper bolt and washers is

found, prior to further flight, replace the bolt

nut with a new or serviceable part in

accordance with the alert service bulletin.

Thereafter, repeat the inspection

(verification) specified in paragraph (a)(2) of

this AD at intervals not to exceed 18 months.

(B) If any damage or discrepancy of the

tangential link upper bolt and washers is

found, prior to further flight, replace the

damaged or discrepant part with a new or

serviceable part, and replace the bolt nut

with a new or serviceable part, in accordance

with the alert service bulletin. Thereafter,

repeat the inspection (verification) specified

in paragraph (a)(2) of this AD at intervals not

to exceed 18 months.

(b) Replacement of the safety links with

modified safety links in accordance with

Boeing Service Bulletin 747–71–2206, dated

April 16, 1987; or Boeing Service Bulletin

747–71–2206, Revision 1, dated November

12, 1987, as revised by Boeing Notice of

Status Change No. 747–71–2206 NSC 1,

dated December 4, 1987, and Boeing Notice

of Status Change No. 747–71–2206 NSC 2,

dated March 17, 1988; constitutes

terminating action for the repetitive

inspection requirements 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, Seattle

Aircraft Certification Office (ACO), FAA,

Transport 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, Seattle ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(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) The inspections, replacement, and

follow-on actions shall be done in

accordance with Boeing Alert Service

Bulletin 747–71A2277, dated November 29,

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 Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington 98124–

2207. Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

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

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(f) This amendment becomes effective on

February 16, 1996.

Issued in Renton, Washington, on January

22, 1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–1572 Filed 1–31–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–02–AD; Amendment

39–9497; AD 96–03–02]

Airworthiness Directives; Boeing

Model 767 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Boeing Model 767

series airplanes. This action requires

inspections to detect cracking and

corrosion of the aft trunnion of the outer

cylinder of the main landing gear (MLG)

and various follow-on actions. This

action provides for termination of the

inspections by repairing the outer

cylinder and installing new aft trunnion

bushings. This amendment is prompted

by a report of the collapse of the right

MLG due to fracture of the aft trunnion

outer cylinder. The actions specified in

this AD are intended to prevent the

collapse of the MLG due to stress

corrosion cracking of the aft trunnion of

the outer cylinder.

DATES: Effective February 16, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February

16, 1996.

Comments for inclusion in the Rules

Docket must be received on or before

April 1, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

02–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from Boeing

Commercial Airplane Group, P.O. Box

3707, Seattle, Washington 98124–2207.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

James G. Rehrl, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Transport Airplane Directorate, Seattle

Aircraft Certification Office, 1601 Lind

Avenue, SW., Renton, Washington

98055–4056; telephone (206) 227–2783;

fax (206) 227–1181.

SUPPLEMENTARY INFORMATION: The FAA

recently received a report of the collapse

of the right main landing gear (MLG) of

a Boeing Model 767–300ER airplane

while the airplane was taxiing in a low

speed right-hand turn. Investigation

revealed that the cause of the collapse

of the MLG was attributed to the

fracture of the aft trunnion outer

cylinder due to stress corrosion

cracking. The cracking initiated at the

crossbolt hole, which is approximately