Federal Register / Vol. 60, No. 244 / Wednesday, December 20, 1995 / Rules and Regulations 65521

and limitations of this AD as applicable. If

the number of operational cycles-per-hour

determined for a replacement shaft assembly

does not equal or exceed 20 cycles-per-hour,

the Rotorcraft Flight Manual limitation

specified in paragraph (g) and the placard

specified in paragraph (h) may be removed.

(j) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used when approved by the Manager, Boston

Aircraft Certification Office, FAA, New

England Region. Operators shall submit their

requests through an FAA Principal

Maintenance Inspector, who may concur or

comment and then send it to the Manager,

Boston Aircraft Certification Office.

Note 5: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Boston Aircraft

Certification Office.

(k) 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 helicopter

to a location where the requirements of this

AD can be accomplished.

(l) This amendment becomes effective on

January 4, 1996.

Attachment—Inspection Results Report

The following information must be

reported as soon as possible, but no later

than 7 days after inspection, to:

Manager, Boston Aircraft Certification

Office, Engine and Propeller Directorate,

Aircraft Certification Service, Federal

Aviation Administration, 12 New

England Executive Park, Burlington, MA

01803–5299, FAX: (617) 238–7199.

Operator/Repair Station lllll

Aircraft Model No. lllll

Aircraft Serial No. lllll

Date of Inspection lllll

Main Rotor Part No. lllll

Main Rotor Serial No. lllll

Type of Aircraft Utilization:

Passenger Carry lllll

Utility/Construction lllll

Firefighting lllll

Logging lllll

Other lllll

Identify Operational Usage Cycles-PerHour:

1–6 Operational Cycles-Per-Hour

lllll

7–19 Operational Cycles-Per-Hour

lllll

20–Above Operational Cycles-PerHour lllll

Next Inspection Date (Estimated):

lllll

and Flight Hours (Estimated):

lllll

Magnetic Particle Inspection (MPI)

Results (this inspection):

Passed lllll Failed lllll

If a crack is found, indicate the

approximate location on the part

and the length of the crack in

inches: llllll

Total Time-In-Service (TIS) (Hours):

Estimated lllll

Actual lllll

Unknown lllll

At Retirement lllll

Inspection results at retirement (if

known):

MPI Passed lllll

Failed lllll

Visual Passed lllll

Failed lllll

Log Book Entry for Part No. lllll,

Serial No. lllll, is (date)

lllll, at Retirement Hours

lllll. This part’s Serial No.

has been marked unairworthy and

unfit for further service on (date)

lllll, 199 ll.

Issued in Fort Worth, Texas, on December

13, 1995.

Daniel P. Salvano,

Manager, Rotorcraft Directorate, Aircraft

Certification Service.

[FR Doc. 95–30772 Filed 12–19–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–238–AD; Amendment

39–9465; AD 95–26–07]

Airworthiness Directives; Bombardier

Model CL–600–2B19 (Regional Jet

Series 100) 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 Bombardier Model

CL–600–2B19 series airplanes. This

action requires revising the Limitations

Section of the Airplane Flight Manual to

provide the flight crew with procedures

to check the travel range of the aileron.

This action also requires inspection for

damage of the shear pins of the aileron

flutter damper and aileron hinge

fittings, and various follow-on actions.

This amendment is prompted by reports

of failure of shear pins in the aileron

flutter damper. The actions specified in

this AD are intended to prevent damage

to the aileron hinge fittings due to failed

shear pins, which subsequently could

cause reduced controllability of the

airplane.

DATES: Effective January 4, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 4,

1996.

Comments for inclusion in the Rules

Docket must be received on or before

February 20, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 95–NM–

238–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from

Bombardier, Inc., Canadair, Aerospace

Group, P.O. Box 6087, Station Centreville, Quebec H3C 3G9, Canada. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, New York

Aircraft Certification Office, Engine and

Propeller Directorate, 10 Fifth Street,

Third Floor, Valley Stream, New York;

or at the Office of the Federal Register,

800 North Capitol Street, NW., suite

700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Franco Pieri, Aerospace Engineer,

Airframe Branch, ANE–172, FAA,

Engine and Propeller Directorate, New

York Aircraft Certification Office, 10

Fifth Street, Third Floor, Valley Stream,

New York 11581; telephone (516) 256–

7526; fax (516) 568–2716.

SUPPLEMENTARY INFORMATION: Transport

Canada Aviation, which is the

airworthiness authority for Canada,

recently notified the FAA that an unsafe

condition may exist on certain

Bombardier Model CL–600–2B19

(Regional Jet Series 100) series

airplanes. Transport Canada Aviation

advises that it has received reports

indicating that the shear pins of the

aileron flutter damper had failed.

Investigation revealed that the shear

pins had sheared off and migrated out,

which subsequently damaged the

aileron hinge fittings. This condition, if

not corrected, could result in reduced

controllability of the airplane.

Bombardier has issued Canadair

Regional Jet Alert Service Bulletin S.B.

A601R–27–058, Revision ‘‘A,’’ dated

September 8, 1995, which describes

procedures for:

1. A visual inspection to detect

damage of the shear link, the shear pin,

and the aileron attachment fitting;

2. Repair of the aileron attachment

fitting, if necessary;

3. For airplanes on which any

damaged shear pin is found, removal of

the aileron flutter dampers, the shear

links, the pivots, and the attaching

hardware;

4. For certain airplanes on which no

damaged shear pin is found, repetitive

visual inspections to detect damage of

the shear link, the shear pin, and the

aileron attachment fitting until the

aileron flutter dampers are removed.
65522 Federal Register / Vol. 60, No. 244 / Wednesday, December 20, 1995 / Rules and Regulations

Transport Canada Aviation classified

the alert service bulletin as mandatory,

and issued Canadian airworthiness

directive CF–95–14, dated September

11, 1995, in order to assure the

continued airworthiness of these

airplanes in Canada.

This airplane model is manufactured

in Canada and is type certificated for

operation in the United States under the

provisions of section 21.29 of the

Federal Aviation Regulations (14 CFR

21.29) and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

Transport Canada Aviation has kept the

FAA informed of the situation described

above. The FAA has examined the

findings of Transport Canada Aviation,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, this AD is being issued to

prevent damage to the aileron hinge

fittings due to the failure of the shear

pins, which could cause subsequent

reduced controllability of the airplane.

This AD requires revising the

Limitations Section of the FAAapproved Airplane Flight Manual to

provide the flight crew with procedures

to check the travel range of the aileron

prior to the first flight of the day. Such

checks are necessary to verify proper

operation of the aileron control system.

The FAA has determined that these

checks may be properly performed by

pilots because the checks do not require

the use of tools, precision measuring

equipment, training, pilot logbook

endorsements, or the use of reference to

technical data that are not contained in

the body of the AD.

This AD also requires a visual

inspection to detect damage of the shear

link, the shear pin, and the aileron

attachment fitting; and repair of the

aileron attachment fitting, if necessary.

This AD also requires removal of the

aileron flutter dampers, the shear links,

the pivots, and the attaching hardware

for airplanes on which any damage to

the shear pin is detected. For certain

airplanes on which no damaged shear

pin is found, this AD provides for

accomplishment of the visual

inspections on a repetitive basis until

the aileron flutter dampers are removed.

These actions are required to be

accomplished in accordance with the

alert service bulletin described

previously.

Operators should note that, although

the relevant Transport Canada Aviation

airworthiness directive requires the

visual inspection of all aileron flutter

damper shear pins and aileron hinge

fittings within 7 calendar days or at the

next scheduled shear pin replacement,

this AD requires that inspection to be

performed within 30 days. The FAA has

determined that an interval of 30 days

will address the identified unsafe

condition in a timely manner. In recent

communications with Transport Canada

Aviation and the manufacturer, the FAA

finds that the unsafe condition was not

as urgent as it initially appeared to be.

In developing an appropriate

compliance time for this AD, the FAA

considered not only the manufacturer’s

recommendation, but also the average

utilization of the affected fleet and the

time necessary to perform the required

actions (10 work hours). In light of all

these factors, the FAA finds 30 days to

be an appropriate compliance time for

initiating the required actions in that it

represents the maximum interval of

time allowable for affected airplanes to

continue to operate without

compromising safety.

This is considered to be interim

action. Once a terminating modification

is developed, approved, and available,

the FAA may consider additional

rulemaking.

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–238–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:
Federal Register / Vol. 60, No. 244 / Wednesday, December 20, 1995 / Rules and Regulations 65523

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

adding the following new airworthiness

directive:

95–26–07 Bombardier, Inc. (Formerly

Canadair): Amendment 39–9465. Docket

95–NM–238–AD.

Applicability: Model CL–600–2B19

(Regional Jet Series 100) series airplanes,

serial numbers 7003 through 7079 inclusive;

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 damage to the aileron hinge

fittings due to failure of the shear pins, which

could cause subsequent reduced

controllability of the airplane; accomplish

the following:

(a) Within 7 days after the effective date of

this AD, revise the Limitations Section of the

FAA-approved Airplane Flight Manual

(AFM) to include the following. This may be

accomplished by inserting a copy of this AD

in the AFM.

‘‘Before engine start, prior to the first flight

of each day, the flight crew or certificated

maintenance personnel shall perform a check

of the travel range of the aileron as follows:

Aileron—Check travel range (to approx 1⁄2

travel) using each hydraulic system in turn,

with the other hydraulic systems

depressurized.’’

Note 2: This AFM revision may also be

accomplished by inserting a copy of

Temporary Revision RJ/45, dated September

7, 1995, in the AFM. When this temporary

revision has been incorporated into general

revisions of the AFM, the general revisions

may be inserted in the AFM, provided the

information contained in the general

revisions is identical to that specified in

Temporary Revision RJ/45.

Note 3: Operators should note that

operation of the aircraft remains restricted to

the altitude and airspeed limits currently

specified in the FAA-approved AFM,

Revision 34, Chapter 5, Abnormal

Procedures, Section 13, Hydraulic Power,

Paragraphs ‘‘A’’ through ‘‘C’’ and ‘‘M’’

through ‘‘O.’’

(b) Perform a visual inspection to detect

damage of the shear link, the shear pin, and

the aileron attachment fitting, in accordance

with Canadair Regional Jet Alert Service

Bulletin S.B. A601R–27–058, Revision ‘A,’

dated September 8, 1995, and at the time

specified in paragraph (b)(1) or (b)(2) of this

AD, as applicable.

(1) For airplanes having serial numbers

7003 through 7054 inclusive: Inspect at the

next scheduled shear pin replacement, but no

later than 30 days after the effective date of

the AD.

(2) For airplanes having serial numbers

7055 through 7079 inclusive: Inspect at the

next scheduled shear pin replacement, but no

later than 400 flight hours after the effective

date of the AD.

(c) If no shear pin is found to be damaged

during the inspection required by paragraph

(b) of this AD, accomplish the requirements

of either paragraph (c)(1) or (c)(2), as

applicable, at the times specified:

(1) For airplanes having serial numbers

7003 through 7054 inclusive: At the next

scheduled shear pin replacement, but no

later than 400 flight hours after

accomplishing the inspection specified in

paragraph (b) of this AD, remove the aileron

flutter dampers, shear link, and pivot, in

accordance with Canadair Regional Jet Alert

Service Bulletin S.B. A601R–27–058,

Revision ‘A,’ dated September 8, 1995.

Following removal of the flutter dampers, the

shear pin replacement in accordance with the

FAA-approved maintenance program is not

required.

(2) For airplanes having serial numbers

7055 through 7079 inclusive: Repeat the

inspection required by paragraph (b) of this

AD at intervals not to exceed 400 flight

hours. At the next scheduled shear pin

replacement, but no later than 1,500 landings

after accomplishing the initial inspection

specified in paragraph (b) of this AD, remove

the aileron flutter dampers, shear link, and

pivot, in accordance with Canadair Regional

Jet Alert Service Bulletin S.B. A601R–27–

058, Revision ‘A,’ dated September 8, 1995.

Following removal of the flutter dampers, the

shear pin replacement in accordance with the

FAA-approved maintenance program is not

required.

(d) If any shear pin is found to be damaged

during the inspection required by paragraph

(b) of this AD, prior to further flight, remove

the aileron flutter dampers, shear link, and

pivot, in accordance with Canadair Regional

Jet Alert Service Bulletin S.B. A601R–27–

058, Revision ‘A,’ dated September 8, 1995.

Following removal of the flutter dampers,

shear pin replacement in accordance with the

FAA-approved maintenance program is not

required.

(e) If any aileron hinge fitting is found to

be damaged during the inspection required

by paragraph (b) of this AD, prior to further

flight, repair in accordance with Canadair

Regional Jet Alert Service Bulletin S.B.

A601R–27–058, Revision ‘A,’ dated

September 8, 1995.

(f) 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, New York

Aircraft Certification Office (ACO), FAA,

Engine and Propeller Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, New York ACO.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

(g) 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.

(h) The inspections, removal, and repair

shall be done in accordance with Canadair

Regional Jet Alert Service Bulletin S.B.

A601R–27–058, Revision ‘A,’ dated

September 8, 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 Bombardier, Inc., Canadair,

Aerospace Group, P.O. Box 6087, Station

Centreville, Quebec H3C 3G9, Canada.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

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

FAA, New York Aircraft Certification Office,

Engine and Propeller Directorate, 10 Fifth

Street, Third Floor, Valley Stream, New York;

or at the Office of the Federal Register, 800

North Capitol Street NW., suite 700,

Washington, DC.

(i) This amendment becomes effective on

January 4, 1996.

Issued in Renton, Washington, on

December 13, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–30961 Filed 12–19–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–245–AD; Amendment

39–9464; AD 95–26–06]

Airworthiness Directives; McDonnell

Douglas Model MD–11 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 McDonnell

Douglas Model MD–11 series airplanes.

This AD requires either that the control

circuit breaker of the left fuel pump

valve be opened and collared, or that

the Airplane Flight Manual (AFM) be

revised to prohibit autoland operation